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Full text of "Mercury capsule no. 14, configuration specification (Mercury-Little Joe No. 5(A)"

Control No. C-53598 



COPY NO. 




DATE 



REVISED 



20 JANUARY 1961 



ASA Use Only 



REPORT 







MERCURY CAPSULE NO. 14 
CONFIGURATION SPECIFICATION 
(MERCURY-LITTLE JOE NO. 5A) 
(Title Unclassified) 



6603-14 ^ 



SERIAL NO. 



.r-6 



PfiOPEerir 



MCDONNELL 



^Mcu^^^yu^ ^<^^^^ 



WfSAJise Only ^^^o^^os 



GODMSD m 



This matenfl^^atains informat 
" ^ ^ defense of thell|l|fced States 
k. ,, Espionage. Loy^^,' 
^ij, ^ ^he transmission or 
'^^:.A'M unauthorized Qg0Kh is ^ 



ng the national 

the meaning of the 

, Sections 793 and 794. 

of which in any manner to 

ed by law. 



SUBMITTED UNDER 



National Aeronautics and Space Administration 

) UNDER — «— ' — ^ 

f A/ p^ £ /^ Contract NAS 5-59^ 



PREPARED BY 



APPROVED BY 



^^ ^ ^^i-^^Z^^4^ 



APPROVED BY 




■y. 



'4Mi^ 



R. D. Korando 2- ^ f)^ HL) o-ufj 



E. M. Flesh 



APPROVED BY 



L. M. Parker 



<»-....._ 



I MUmWM^ »» ft 
{NASA-CR-50068) HEBCUHI CAPSULE BO. 14, 
CCNFIGUBATICH SPECIFICATIOM (HEBCUBY-LIITLE 
JOE NC. 5(A) (HcDonnell Aircraft Co.) 
^"^ P Unclas 

00/99 29009 



HTa-T^I 549^111 




nAT» 20 January 196l 
REVISH) 



MCDONNELL 



^^^'uteum- Lcy^oui£an 



PAGC 



ST. LOMS, MISSOUII 



RCPORT 



g6Q^-it^ 



RCVISED 


^3^^S^mrffiBtaM 


iyiooaMercury CapstiLe 




TABLE OP COHTEKTS 




PARAGRAPH 


TITLE 


PAGE NO. 


Title Page 






1.0 


SCOPE AHD CLASSIPICATIOR 


1 


1.1 


Scope 


1 


1.1.1 


Mission 


1 


2.0 


APPLICABLE SPECIFICATIONS AMD OTHER PUBLICATIQHS 2 | 


2.1 


References 


2 


2.2 


Process Specifications 


2 


2.3 


Contract Change Proposals 


3 


2.U 


Request for Alteration 


5 


3.0 


REQUIREMErrrS 


7 


3.1 


Characteristics 


7 


3.1.1 


Velght and Balance 


7 


3.1.1.1 


Gross Weight 


7 


3.1.1.2 


Abort Wei^t 


7 


3.1.1.3 


Impact Wei^t 


7 


3.1.1.4 


Weight and Balance Summary 


8 


3.2 


General Description 


10 


3.2.1 


Configuration 


10 


3.2.2 


Selection of Materials 


10 


3.2.3 


Fabrication 


11 


3.2.U 


Interchangeabillty suod Replaceability 


11 


3.2.5 


Finish 


11 


3.2.6 


Identification suod Marking 


11 


3.2.7 


Extreme Environmental Requirements 


11 


3.2.8 


Lubrication 


11 


3.2.9 


Reliability 


12 


3.3 


Aerodynamic and Hydrodynamic Considerations Ih \ 


IX 


Structural Design Criteria 


U 


3.5 


Capsule 


15 


3.5.1 


Description 


15 


3.5.2 


Construction 


15 


3.5.3 


Entrance and Emergency Egress Hatch 


15 


3.5.1* 


Exit Hatch 


15 


3.5.5 


Window 


15 


3.5.6 


Antenna Fairing 


16 


3.5.7 


Antenna Cover 


16 


3.6 


Heat and Micrometeorite Shielding 


17 


3.6.1 


Porebody Heat Protection 


17 


3.6.2 


Afterbody Heat Protection 


17 


3.6.3 


Micrometeorite Protection 


17 


3.7 


Booster Adapter 


18 


3.8 


Crew Station 


19 



MAcaat CM no MAN 9*1 



r>ATB 20 January IQgl 

REVISED 

REVISH) 



MDOMEIL 



',.^'aitftfflr Ld^bouSttan 



PAGE 



Ji 



FARAGRAFE 



3.8.1 

3.8.1.1 

3.8.1.2 

3.8.2 

3.8.3 

3.8. 1^ 

3.8.5 
3.8.6 

3.8.7 
3.8.8 

3.8.9 

3.9 

3.9.1 

3.10 

3.10.1 

3.10.2 

3.10.3 

3. 10. If 

3.11 

3.11.1 

3.11.2 

3.11.3 

3.12 

3.12.1 

3.12.2 

3.12.3 

3.I2.U 

3.12.5 

3.12.5.1 



ST. LOWS, MISSOUM 



REPORT 



6603-U 



AurtoB Mercury Capsiile 



TABLE OF COHTEHTS (Continued) 

TITLE 



Consoles 

Rlght-Easd Console 

Left -Hand Console 

Instrumentation and Displays 

Time Reference Indication 

Angular Rate and Altitude Indicator 

Sequence System and Override Controls 

Dead Reckoning Earth Path Indicator 

Switches and Handles 

Switch Fuses 

Lighting 

Capsule Environmental Control 

Environments^. Control System 

Stabilization Control Subsystem 

Automatic Stabilization and Control System 

Rate Stabilization and Control System 

Horizon Scanner 

Reaction Control System 

Retrograde Rocket Systiem ' 

Description 

Installation 

Fosigrade Rocket System 

Escape System 

Description 

Escape Rocket 

Pylon Jettison Rocket 

Escape System Pez^ormance 

Escape System Sequence 

nbzmal Mission 



PAGE NO. 



19 
19 
19 
19 
20 
20 
20 
22 
22 
23 
23 
25 
25 
25 
25 
25 
25 
25 
26 
26 
26 
26 
27 
27 
27 
27 
28 
28 
28 



3.12.5.1.1 


Time Sequence 


29 


3.12.5.2 


Aborted Missions 


29 


3.12.5.2.1 


Abort Initiation 


29 


3.12.5.3 


Escape Sequence Off the Pad and Prior to 






Tower Separation . 


29 


3.13 


Electrical Power SuRply System 


31 


3.13.1 


Main Power Supply 


31 


3.13.2 


Standby Power 


31 


3.13.2.1 


Isolated Power 


32 


3.13.3 


A.C. Power 


32 


3.13. 1^ 


Electrical Connectors 


32 


l.llX.I 


IMbllical Connections 


32 


3.U 


Communications Systems 


35 



MAC 231 CM (10 MAR M) 



nATP PO JapTiarv 196l 

REVISED 

REVISED 



MCDONNELL 



'_x''«4ff«iap^ Loybotd&m 



PAGE 



iii 



PARAGRAPH 



3.14.1 
3.11^.2 
3.11^.3 
3.lV.l^ 

3.H*.5 
3.ll^.6 

3.1^.7 
3.1'*. 7.1 
3.1'*. 8 

3.li*.9 

3.1i*.lO 

S-li^.n 

3.15 

3.15.1 

3.15.2 

3.15.2.1 

3.15.3 

3.15.3.1 

3.15.3.2 

3.15.1* 

3.16 

3.16.1 

3.17 

3.17.1 

3.17.1.1 

3.17.1.2 

3.17.1.3 

3.17.1.4 

3.17.2 

3.17.2.1 

3.17.2.2 

3.17.2.3 

3.17.2.1* 

3.18 

3.19 
3.20 

1*.0 
l*.l 
1*.2 



ST. LOWS, MIS 




REPORT 



6603-11* 



Mooa Mercury Capsule 



TABLE CF COIilTENTS (Continued) 
TITLE 



QnAUFICATIOIT 
MAC Qoallflcation 
IIASA Qualification 



PAGE NO. 



Low Frequency Telanetry Transmitter 


35 


Higji Frequency Telemetry Transmitter 


35 


Telaaeter Power Supply 


35 


Telemetry Line Filter 


35 


C-Band Beaton 


36 


C-Band Antenna 


36 


Blconlcal Antenna 


36 


Multiplexer 


36 


UHF Descent Antenna Array 


36 


Communications Control Panel 


36 


Coaxial Switches 


37 


Coaxial Caljles and Connectors 


37 


Recording Equipuent 


38 


Cameras 


38 


Tape Recorder 


38 


Commutated Data Recording 


38 


Voltage Controlled Sobcarrler Oscillators 


39 


Concpensating Oscillators 


39 


Mixer Anrplifier 


39 


Special Instrumentation 


39 


Navigational Aids 


1*1 


Periscope 


1*1 


Landing and Post-Landing Systems 


1*3 


Tiandlng System 


1*3 


Drogue Parachute System 


1*3 


Main Parachute System 


1*3 


Pilot Parachute 


l*i* 


Reserve Parachute 


4i* 




1*5 


SOFAR Boob 


1*5 


Fluorescein Dye Marker 


1*5 


Recovery Flashing Id^t 


1*5 


Impact Sensor 


1*5 


HaTnillng Provisions 


1*6 


Svipport Equipment 


ke 


Pyrotechnics 


1*6 



1*7 
1*7 
1*7 



MAcaai CM no MAW Ml 



DATE 



20 Jazmary I961 



MCDONNELL 



REVISB) 
REVISED 



PARAGRAPH 



5.0 

5.1 
5-2 

6.0 

APPESDJX 
I-A 



APPENDIX 
I-B 



APPENDIX 
I-C 



APPENDIX 
I-D 



Zipn^ie*^ Loytotdtion. 



ST. LOMS, MUSSOUn 



PAGE 


iv 


REPORT 


66o?.ilt 


MODPi Mercury Capsule 



TABLE OF COTTTEiyrS (Continued) 
TITLE 



TESTIHG 
MAC Testing 
NASA Testing 

DEPmrrions 



Govemment-Pumished Equipment - 
Contractor Installed 



Govemment -Furnished Equipment 
Government Installed 



Contractor -Furnished Equipment - 
Contractor Installed 

Item 1 - General 

Item 2 - Rocket Installations 

Item 3 - Airborne Equipment 

Item h - Electrical 

Item 5 - Automatic Stabilisation and 

Control System 
Item 6 - Reaction Control System 
Item 7 - Communications 
Item 8 - Environmental Control System 
Item 9 - Instrumentation 
Item 10 « Landing and Fost--Landing System 
Item 11 - Pyrotechnics 



Contractor -Furnished Equipment - 
Govemment Installed 



PAGE NO. 



47 

1^7 
47 

^1 



W 



^9 



50 
5^^ 

56 
68 

^ 
70 

71 
73 
75 
78 



80 



MAC Zai CM (10 MAff SSI 



HATP 20 January 

REVISED 

REVISED 



^ MMNM^^ 



iotdtunt PAGE z. 

ST. MUlS, MISSOUII REPORT ^^^3-1^ 



TABLE OF FIGURES 



Block Diagram 



Mnngi Mercury Capsule 



FIGUPE 


TITLE 


PAGE NO 


1 


General Arrangement 


6 


2 


Atmospheric Properties 


13 


3 


Instrument Panel and Consoles 


2lf 


If 


Seqrieatial Scbeoatlc 


30 


5a 


D.C. Power Control System 


33 


5b 


D.C. Power Control System 


31^ 


6 


Basic Instrumentation Systaa 


uo 



MAC 231 CM (10 MAR SSI 



REVISH) St. l ows, MISSOjIt tM, REPORT 6603^lk . 

REVISB) ^^WPff ^f WKfrl 1 AL MOOa Mercury Capstile 



1.0 SCOPE Aim CLASSIFICATION 

1.1 SCOPE - This configuration specification shall define the details 
of design, construction, and equipment requirements for an 

Instrumented Capsule (MAC No. lVU-5A) as follovs: 

NASA Designation Project Mercufcy 

Designer's Name McDonnell Aircraft 

Corporation (MAC) 

Model Designation Model 133K 

Number and Places for Crew One Cabin Enclosure 

Launch Vehicle Little Joe Booster 

1.1.1 MISSION - The purpose of Little Joe No. 5A shall be to qualify 
the Mercury Capsule escape system and other systems which must 
function during and after escape at the cooibination of dynamic pressure, 
Mach ntmiber, altitude and flight path angle that represent the most severe 
conditiozis that can be anticipated during an orbital launch on an Atlas 
booster. Pligjit trajectories or other calculations will be based on atmos- 
phere given in Figure 2. 

1.1.1.1 The objectives of the bfiillistic test fli^t of Capsule Nb. ik in 

combination with a modified Little Joe booster sheuLl be as 
follows: 

a. Demonstrate the performance of the capsule escape system 
and other systems which must perform during and after an 
escape maneuver. 

b. Demonstrate the structural integrity of Merctiry Capsule and 
escape system during an escape initiated at the highest 
dynamic pressure that can be anticipated during an Atlas 
launch for orbital fli^t. 

c. Determine the fli^t dynamic characteristics of Mercury 
Capsule in an escape maneuver. 

d. Establish the adequacy of the capsule landing ^* nd recovery 
system* 

e. Establish the suitability of the capsule recovery procedures. 

^> 

f . Establish prelaunch checkout procedures for the functioning 
capsule systems. 



„,„ z^^^n^is^. MCDONNELL ^ ^^^^^^ ,^ . 

REVfSB) ST. LOWS. MISSCMML IMPORT 6603-l^ 



REVISH) - ^Wfl^W^i^HSCE A^nna Mercury Capsiae 



2.0 APPLICABLE SPEdFIGATIOgrS AND OTBSR PUBLICATIOMS • McDonnell 
Aircrafl; Corporation's prime objective relative to Government 

specifications Rhall be in compliance with applicable documents to the most 
practicable extent, with the object of providing an optimum operational 
vehicle within the specified time schedule. 

2.1 REFERENCES - OSie following documents are referenced herein: 
MAC Report Ho. 6^95, ''Project Mercury Specification Applica- 
bility Criteria", dated ^ Deceaber 1959^ Revised 1 July 1959. 

MAC Dravlng Ho. ^5-00003^ "Qualification Status List". 

rnSA Specification Ho. S-6, "Specification for Manned Space 
Capsule", Revised 26 Janiaary 1959* 

2.1.1 In event of a discrepancy between this document and any 

document referenced herein, this specification shall talce 
precedence. 

2.2 PROCESS SPECIFIGAIIOHS - The following MAC Process Specifica- 
tions shall apply specifically to the Project Mercury capsule 

herein: 

P.S. Ho. IITLE 

11051 Cemeating of Heat Blankets for Model 133 

1122^ Sealing of Model 133 Capsule 

12301 GGLeaning of Model 133 Environmental Control Systea Lines and 
Honoperating Componeats > 

12kS0 Chrcmic Acid Zreataent of Aluminum lEanks for Model 133 

1321^ Black OrLde Finish for High Hnisslvlty for Model 133 

1333^ Preparation and Application of Coatings to Interior Sxarfaces of 
Sealed Cabin Area of Model 133 

13^30 Erterior Paint Finishing of Mbdel 133 Capsules 

1^39 Imbrication of Model 133 Otower Insulation 

16001.5 Marking of Model 133 Parts and Assemblies 

170^ Care, Handling, Storage and Assembly of Model I33 Glass 

17172 Waterproofing of Electrical Connectors for Continuous Operating 
Temperature up to 5OOOF 



MAC 231 CM (IOMAItM» 



REVISB) ST, LOUIS. MiSSOUM REPORT 66Q2zlit 

REVISED , JBB^WHDKWWfHf^ MOoa Mercury Capsule 



2.2 PROCESS SPECIFICAriQNS - (Continued) 

P,S> No> TITLE 

17305 Sealing of Printed Wiring for Model 133 Fli^t Test 
Instrumentation 

17^30 Installation of Electrical Wiring in Model 133 

17^10 Fabrication of Electrical Wire Assemblies for Model 133 

17^10.1 Assembly of Electrical Cable Terminals and Splices for Model 133 

17^10.2 Assembly of Electrical Connectors for Model 133 

17^10.3 Assembly of Radio Frequency Cables for Model 133 

2QIO6 Storage and Handling of Silver Zinc Batteries for Model 133 

20113 Care, Handling and Storage of Model 133 Pyrotechnics 

2020U Reopair for Skin Puncture on Model 133 Capsiale Wall 

20500 Fabrication and Housekeeping Policies i^licable to Model 133 

20501 Requirements for Special Assembly Areas for Model 133 

20505 Storage and Handling of Model 133 Environmental Control System 

21030 Leak Testing of Model 133 Structural Assmblies 

21311 Incoming Inspection of Model 133 Space Capsxile Coatings 

22810 Soft Soldering of Electrical Connections for Model 133 

23502 Acceptance Procedure for Model 133 Forward Viewing Window 
Assembly 

2.3 CQHTRAgl CHARGE PROPOSALS - The following Contract Change 
Proposals (CCP*sj 3aave been incorporated and shall be considered 

basic to this configuration specification as approved through negotiation 
with NASA: 

CCP TITLE 

3 Posigrade Rocket Installation 

1^1 Reefed Ring - Sail Landing Parachutes, Installation of 



MACSSt ON (lOMARMt 



DATE go ^BBwry 1961 M^DOMEIX ,^^ ^ Cybctdilm page k 

REvisa ST. lows, Missoun Report 6603^ 

REVISB) /^WflflfBfill ii l i iil MODa Mercury Capsule 



2.3 COHTRACT CHAIK2B PROPOSALS - (Continued) 

CCP TITLE 

42 Orbit Ligjit; Specification Requirement Deletion 

I4.3 Instrumentation Changes; Subcarrier Oscillator and Conmnitator 
Replacements 

1*4 lizrpact Pressure Measurement; Deletion of Requirement 

W Lov Pover Telemetry, Power Output Increase 

38-1 Astronaut Ekuergency Egress Hatch Installation 

66 Communications Systons; Frequency Changes 

73 Astronaut Observation Window Installation 

IS Rescue Aids Switch By-Pass Relay and By-Pass Switch for 30 Second 

Retro Firing Delay 

76 Main Instrum^Qt Panel Redesign 

84 Telemetering of Poslgrade Rocket Firing 

91 Elimination of Mlnitrack/Microlock Beacon 

93 SQPAR Bomb Installation 

98 Smoke Recovery Aid; Removal of 

IQL Post Landing OperationcO. Sequence Change for Capsule 
Instrumentation 

113 Modifications to Escape Tower 

217 Capsule Dye Marker Change 

226 Incorporation of a 5 psi Differential Cabin Pressure Control 
Valve 

238 Modification of Capsule l4 and Support for Little Joe 5 "A" 
Mission 

239 Triple Nozzle Installation on Jettison Rockets 



MACaSf CM (10 MAN SSI 



PAGE 



^„ ^ .anu^ 1^ MCDONNELL ^ ^^^^^ 

REVISED . ST. LOWS. MISSOUM REPORT 6603=3^ 

REVISED- 4|fifiilPMRII^RHnr A^ncL Mercury Capsxile 



2 A REQUEST FOR AUEE^ATIOH - The following requests for alteration 

recommended diiring the Development Engineering Inspection (DEI) 
of Project Mercury Capsule Ho, T> on 16 August throu^ l8 August I960, have 
been incorporated. 

RPA No. SUBJECT 



30* 


Capstile Booster Uiabilical Door 


kk 


Cabin Fresstire Control 


62 


Trade Assignments 


91 


Sea Marker Dye 



* Weight change only. 



MAC 231 CM (10 MAII Stl 



DATL 



20 Jowiiqry ]9j] 



J!!l MfiSLL/ 




PAGE 



0...^.^.^: MCDONNELL ^ ^^.^ 

REVISH) ST. LOUIS, MISSOUW _ REPORT ^O^a^ 

REVISED ^!lWP^FIlBi"i'l*»»L "^ MOOa Mercury Capstil e 



3.0 REQUIREMENTS 

3.1 CHARACTERISTICS 

3-l*l WKiUiiT AM) BALAHCE - Specification MIL-W-251^ and Technical 
Order l-lB-40 shall be utilized as reference guides* 

3.1«1.1 GROSS WEIGHT « Such ballast shall be added in a manner to 

obtain weight and center of gravity location similar to the 
manned orbital capsules or the launch weight and center of gravity of 
Mercury Capsule No. 3* 

Actual weight breakdown and center of gravity of the capsule 
as described herein are Included. 

3.1.1*2 ABORT WEIGHT - Abort weight is defined as the gross latmch 

weight of the Project Mercury No. Ik capsule less the adapter 
and the retrograde rocket assembly plus the escape system. 

3«l*l-3 IMPACT WEIGHT' - Impact weight is defined as the abort weight 

of the Project Mercioy No. 1^ capsule^ less the main para«* 
chutes^ nose cone assembly^ and SOFAR bomb. 



MACait CM (10 MARS*) 



HATg 20 January 196l 



MCDONNELL 



^^^y^uic^4mf i^oyb&uESpn 



PAGE 



8 



REVISB) 
REVISB) 



ST. lOUIS, MISSOWH 



3.I.IA 



WEIGHT AND BALAHCE SUMMAEy 



(a) Vehicle Weight Breakdown 

HEM 

structure 

Claiqp Ring - Capsule to Adapter 

Escape System 

Unaccoimtable 

Heat Sink 

Reaction Control Group . 

Retrograde System 

Landing System 

Instruments and Navigation Equlpoent 

Electrical Group 

Communications 

EuTlsronmental Control System 

Telemetry and Recording 

Recovery Gear 

Crev and SurvlTal Equipment 

Pallet 

Ballast 

Actual Weight Adjustment 

Gross Weight Launch Vehicle 



REPORT 



6603^1^. 



jytnpPL Merciary Capsul e 



UEIGBT 


BALLASTED TO 
CAFS(JI£ m, 3 
WEKST 


569.39 


569.39 


35.38 


35.38 


101^9.60 


10J»0.62 


-1.32 


-1.32 


31^3.18 


3'^3.l8 


28.02 


28.02 


279.^3 


279.»^3 


181^.82 


18^.82 


91.85 


91.85 


2U4.83 


2l*U.83 


7iv.58 


71V.58 


36.99 


36.99 


68.35 


68.35 


18.57 


18.57 


1.30 


1.30 


182.85 


182.85 


618.19 


51^7 06 


30.85 


30.85 


3856.86 


3776.75 



MACaSI CM IIOMANSM 



DATE PO rTfl.nnftry 19fi1 

REVISED 

REvisro . 



MCDONNELL 



'^x ' & ^g*^ (.Af^oueSoit 



PAGE 



ST. LOINS, MUSSOUn 



REraRT 



6603-ii» 



Mnnn Mercury Capsule 



3.1.1.1* MEIGBT AHD BALAHCB SOMMARI - \ 


[Continued) 






(b) Capsule Nb. ll* Welghrt and BcLLaace Mission History 

nKI.IVKKED 
mm WEIGHT C.G.* 


BALLASTED TO 
CAPSULE NO. 3 
WEIOT C.G.* 


Gross Wel^t-Launch 
Less: 

Clamp Rlng-Adapter to Capsule 
Retrograde^oslgrade Assembly 


3856.86 

-35.38 
-25l*.95 


I72.OT 


3776.75 

-35.38 
-25l*.95 


172.53 


Abort Weight 
Less: 

Escape Rocket FrqpeUant 


3566.53 
-293.20 


178.78 


31*86.1*2 
-293.20 


179.1^l^ 


Abort tfelght-No Fuel 
Less: 
Unaccountable 
Escape Tover 


3273.33 

+1.32 
-756.1*0 


165.53 


3193.22 

+1.32 
-71*7.1*2 


165.91 


Coast Phase Wei{^ 
Less: 

Bbse Cone Assembly 


2518.25 
-80.39 


12l*.12 


21*1*7.12 
-80.39 


12l*.ll 


Main Chute Design Weight 
Less: 

Main Cbute 
SOFAB Bomb 


21*37.86 

-63.83 
-1.98 


121.73 


2366.73 

-63.83 
-1.98 


121.61* 


Impact Welc^ 
Less: 
Reserve Chute 
Pilot Chute 
Dye-Har]&er 


2372.05 

-62.29 
-3.57 
-2.50 


120.1*5 


2300.92 

-62.29 
-3.57 
-2.50 


120.32 


FLotatlon Weight 


2303.69 


119.06 


2232.56 


118.89 


* C.G. Location Is glvem as Z station. Edge 


of heat sink Is Z » 103.1*1*. 



^MAdTaSn' CIV (10 MAH 9Br 



DATE ?n January 1961. M^DOMEIl ,^£ ^ C^tnnd&m PAGE i? 

REVISH) ST. LOWS. MISSO UM l»ORT 6^2=l!t 

REVISED JHBIHTBBBigg^^^ aaohr Mercury Capsule 



3.2 GEHESAL DESCBIFTION 

3.2.1 COHFIGURATIQH - The capsule configuration shall be of the type 
shown in Figure 1 and g^^T t fulfill the requirements specified 

herein. The capsule shall be congDrised of the following: 

a. Structure (See Paragraph 3*^) 

b. Heat and Mcrometeorite Protection (See Paragraph 3 •6) 

c. Booster Adapter and Separation System (See Paragraph 3*7) 

d. Consoles (See Paragraph 3*S«8) 

e. Instrumentation and Display (See Paragraph 3-8«9) 

f . Environmental Control System (See Paragraph 3 •9) 

g. Retrograde Socket System (See Paragraph 3»ll) 
h-J Escape System (See Paragraph 3*12) 

i. Power Supplies (See Paragraph 3*13) 

j« Communication Equipment (See Paragraph 3-1^) 

k. Recording Equipment (See Paragraph 3»15) 

1. Navigational Aids (See Paragraph 3 -16) 

m. Landing and Post Landing System (See Paragraph 3*17) 

n. Posigrade Rocket System (See Paragraph 3«11*^) 

o. Handling Provisions (See Paragraph 3 -18) 

p. Pyrotechnics (See Paragraph 3*20) 

3.2.2 SELECTION CF MA!EEEtIALS - Mission requirements of the capsule 
dictate use of hi^ temperature resistant materials. Heat 

resisting materials such as titanium^ beryllium, steel, nickel base alloy 
(Rene' ^l), and insulation materials such as Thermoflex, Fiberglas and 
ceramic coatings ^VtftTT be used. Where practicable, materials in accordance 
with the requirements of AHA Bulletins liv3d and l47r shall be utilized. 



MACaat CM (10MM»S«» 



DATE 20 January 1961 MiDONNEIl ,^^ ^ C^otd&m. PAGE _11 

REVISED _ CT i^HC ^KOMi^y ^^ REPORT £^Q3=llf 

REVISH) ^ JBllifl^BBftMNi^tfl^^ MOOa Mercury Capsule 



3.2.3 FABRICAnOlT - Structural design concepts of the capsule 

emphasize employment of proven manufacturing techniques and 
methods to the greatest possible extent. Maximum use shall he made of 
developed "off-the-shelf" con5)onents fabricated by dependable subsystea 
manufacturers. McDonnell Aircraft Corporation standards of vorkmanship, 
processes and procedures are based on fabrication of production articles 
according to military standards 

3.2.1|- IMTERCHA3TOEABILITY AMD REPLACEABILITY - The inter changeability 

and replaceability intent of Specification MIL-I-850QA(ASG) shall 
be met on those items of equipment possessing identical physical character- 
istics and functions in relation to capsule usage as defined in MAC Report No, 
61^95, revised 1 July 1959* Interchangeability and replaceability require- 
ments are not considered mandatory on basic capsule structure. Interchange- 
ability and replaceability for those equipment items as set forth in this 
paragraph shall be assured by design requiraaents, natxire of manufactiire, and 
monitoring by contractor personnel, and need not be physically demonstrated 
by the exchange or removal of equipment items from the capsule and replace- 
ment of these items in a formal demonstration. 

3-2.5 FIHISH - Definition of finish requirements shall be as specified 
in the finish specification, McDonnell Drawing Kb. iv5-9CX)00, 

3.2.6 IDENTIFICATIOCT AMD MARKIMI - MIL-STD-I30 shall be considered as 
a reference guide in identification of the capsule and capsule 

components. Marking shall be in accordance with Specification MIL-M-250i^T 
as applicable. MAC Drawing No. ^5-00009 shall define external capsule color 
requirements and shall specify that the words "UNITED STATES" in six inch 
(6") block letters, shall be painted on opposite sides of the capsule. 
Capsule test cable plug or receptacle identification shall be in accordance 
with MAC Drawing No. 45-00010. 

3.2.7 EXTREME KHVlHUHMJiiOTAL REQUIREMEirrS - Trajectory characteristics 
shall be based on the atmospheric density and tesiperature varia- 
tions of ARDC 1959 Model atmosphere. Earlier data, as presented in Figure 2, 
may be used ^en its use Is not critical or when it is conqpatible with ARDC 
1959 Model atmosphere. The capsule, all subsystems, and components shall be 
designed to withstand the environmental conditions which are expected to be 
encountered dturing the mission outlined in Paragraph 1.1.1. 

3^2. 8 LDBRICAIIQN - Lubrication of .components where required shall be 

in accordance with the requirements of Specification MIL-L-688aB. 
Lubrication data shall be included in maintenance handbooks. No petroleum 
base lubricants shall be used. Lubricants shall be of the silicone base, 
fluorolube, oxylube 702, and dry film type. Lubrication shall not cause any 
toxic or flammable substances to occur in the' astronaut's compartment or in 
the environmental control system. 



MAC 231 CM <I0 



PAGE 



DATE 2Q JaBMTT 19^ MtDONNEII ,^^ ^ (j^bctd&m 

REVISED SriOUIS. MISSOUM RETORT 6602zlL 



3.2-9 RELIABILITY - An integrated reliability program shall be con- 

ducted throughout the design, development and fabrication of the 
Mercury capsule. This shall include the salient featxires outlined in 
Specification MIL-W-9411 to the most practicable extent within the scope of 
the program. The design approach shall esrphasize the safety of the mission. 
Although not specified herein in every instance due consideration shall be 
given to siniplicity^ redundancy, and the use of back-up systems in order to 
inrprove mission reliability. 



MAC 231 CM ClOMAffSS) 





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laii 'aonxiiiv sittiiMoao 



REVISED ST. LOmS, MISSOUB I^EPORT 660^^1,k 

REVISED JEBBERHESBBH^ MonH Mercury Capsule 



3.3 AERODiaiAMIC AMD HZDROITMAMIC CONSIDERAIIOHS - Ihe desiga config- 
uration of the capsule described herein relative to aerodynamic 

and hydrodynamic considerations has been based on the following: 

a« !Qie overall capsule configuration at the time of re-entry 
shall be statically stable in the heat sink forward attitude. 

b. Correct attitude during the re-entry phase shall be 
facilitated by use of a destabilizer flap located on the 
top of the antenna fairing opposite the roll axLs horizon 

\ scanner. 

c. An aierodynasiic qpike and ballast assembly shall be provided 
for mounting on top of the escape rocket structural assembly. 
IChis assembly shall reduce supersonic launch and escape drag. 

d. Re-entry forebody shape effect on water and land impact 
loads. 

e* Design landing condition of the capsxile has been based on 
impacts on both water and land, within the structural design 
parameters defixied in M&C Report No. 6693, revised 3 August 
i960. 

f * Xhe capsule shall be bouyant and hydrodynamically stable 
upright in the water^ heat sink assembly down^^ and shall 
be capable of righting itself. 

3.4 SORUCTORAL DESIGH CRITERIA - Structural design criteria of 
Mercury capsule shall be as defined in MAC Report 6693, "^ 

revised 3 August i960 and Paragraphs 2.4 through 2.k.2.3 of NASA Specif icgi- 
tion S-6 revised 26 January 1959- Specifications MIL-A-8629(ASG) and 
MIL-S-^700 (ISAF) series shall be lised as reference guides. 



MAC 391 CM (10 MAM Ml 



HATF 20 January 196l 

REVISED 

REVISED — 



MCDONNELL // . ./^ 



PAGE 



15 



ST. LOUIS, MISSOURI 



REPORT 



6603-1^ 



MQDPL Mercury Capsule 



3.5 CAPSU3J! 

3-5 •! DESCRIPTION - Olie Mercury capsule shall be of a conical configu- 
ration having an extrenely blunt forebody (in the re-entry 
attitude) with booster adapter attachment fi-ttings and an afterbody 'vrtiich 
tapers to a juncture with a cylin4rical section which shall support a truncated 
antenna cone and escape systaa pylon and rockets. The contoxirs of the fore- 
body g>^<^Ti be such as to provide the mft-ynTwiim practical wave drag and uniform 
surface heating consistent with other requirements. The afterbody configura- 
tion fthall augment stability and provide adequate volume^ and low heating as 
well as requirements for parachute stowage and escape system attachment, de 
overall capsule configuration at the time of re-entry shall be stable in the 
normal re-entry angle of attack. Internal volume of the capsule shall be 
based on a human occupant five feet ten and one-half inches (5' - IO-I/2") 
tall and weighing one-hundred and eighty (I80) poiands. 



3.5-2 



CONSTRUCTION - The capsule shall be semimonocoque titanium 



construction consisting of a conical and a cylindrical section. 
The conical section fi>^»T* consist of an xmbeaded inner skin seam welded to a 
beaded outer skin with 2^ equally spaced longitudinal stringers; two bulk- 
heads foim the pressurized cabin area. The cylindrical section shall have a 
single skin with 12 equally spaced stringers and internal shear webs which 
support the parachutes. Die capsule structure shall be protected from heat, 
noise and micrometeorites by insulation and an outer covering of shingles 
plus a heat sink which shall absorb heat dtaring re-entry. 

3.5.3 ENTOMCE AND EMERGENCY EGRESS HATCH - Die entrance and emergency 

egress hatch, in accordance with MAC Drawing No. ^5-35003 
located in the capsule conical section, shall be trapezoidal in shape as dic- 
tated by the capsxile configuration (see Figure l). The hatch assembly shall 
be of construction similar to the basic capsule structure. A dummy explosive 
assembly simulating that shown on MAC Drawing No. 45.35701 shall be incor- 
porated in the hatch assembly. !Ibe dummy explosive assembly shall be moimted 
about the hatch perimeter and shall consist of a gasket type sill. 



3-5.^ 



EXIT HATCH - The exit hatch in accordance with MAC Drawing No. 



45-32023 shall be located in the small afterbody pressinre bulk- 
head. Q3ie hatch shall be dish- shaped and shall be an Inward opening, plug 
type hatch of reinforced aluminum construction. The hatch shall be held in 
p3^ce by a retaining ring which^ when latched in place, shall cause the hatch 
to seal to the small pressure buUdiead. 



3.5.5 



WINDOW - An observation window assembly shall be provided. 



Biis assembly shall be located in the afterbody conical section 
from stations Z124.81 to Zl44.80. Ohe window assembly shall consist of an 
outer window assembly in accordance with MAC Drawing No. 45-35030 and an 



MAC 2St CM (10 MAH SSI 



ST. kOWS, MlSSOUn REPORT ^^3'^^ 

AL MQngL Mercury Capsule 



REVISED 
REVISED 




3.5-5 WIHDOW - (Continued) 

inner window assembly in accordance with MA.C Drawing No. ^5* 35035* Window 
shape shall be trapezoidal as dictated by the capsule conical configuration 
with the base of the trapezoid toward the heat sink end as indicated in 
Figure 1 herein. Ihe outer window asseotbly shall consist of a single pane of 
0*350 inch Vycor glass contoured to the capsule structural shell curvature. 
The outer pane shall possess grade 2N optical fidelity in its two critical 
areas. Grade 2N glass shall peimlt an optical deviation of 2 minutes of arc. 
Location of critical areas shall be such as to be ccmpatible with reference 
sigibt lines on the inner window assembly. The outer pane shall be mounted in 
a structural firame> with suitable sealing gaskets on the inner and outer 
surfaces and spacers supporting the edge inside the f^rame. The inner window 
assembly shall consist of three (3) flat panes of glass of the trapezoid con- 
figuration, each having an optical fidelity of grade 211. The two (2) inner 
panes shall be 0.3^ inch tempered glass and the outermost pane of the inner 
window assembly shall be 0,170 inch Vycor glass. The outermost pane shall 
contain lateral reference sight lines on the inner and outer surfaces. The 
inner window panes shall be mounted in individual supporting rings, inde- 
pendently sealed by gaskets on upper and lower surfaces azid held flim by 
spacers around the edge inside the ring. 13ie pane assemblies shall be sup- 
ported by a structural frame ^tAiich shall be attached and sealed to the capsule 
inner structure. The inner surface of the outer window pane and both stirfaces 
of the inner window assembly panes shall be coated with a single layer of 
magnesium fluoride (H^Fg^ fiM for Impeding thermal radiation in the cabin. 

3.5.6 ASTEMk FAJRHTG - M antenna fairing, in accordance with MA.C 
Drawing No. ^5-31003, shall be installed between the cylindrical 

recovery compartment and the escape tower and shall extend from Sta. ZI8U.57 
to Z208.57* An eight (8) inch window assembly consisting of a silicone base, 
fiberglass insulation, vycor glass, and teflon strips, shall be located aroxmd 
the outer base of the antenna fairing and shall act as a dielectric for the 
main blconical antenna. A destabillzer flap assembly, in accordance with 
MAC Drawing So. 45*-31026, shall be attached to the upper extremity and outer 
edge of the antenna structural assembly. Obe destabillzer flap shall prevent 
the capsule from becoming stable with the heat sink forward. Prior to capsule 
tower separation, the destabillzer flap, which shall be spring loaded to the 
outboard position, shall be held flat against the antenna fairing by means 
of a quick release pin attached to the escape tower. The flap shall be 
released upon escape tower Jettison. Ihe antenna fairing shall be auto- 
matically jettisoned Arom the capsule as the capsule descends to 10,000 feet 
altitude. (See Paxa. 3.17-1»2). 

3.5.7 AHTEMHA. COVER - An antenna cover assembly, in accordance with 
MAC Drawing Ho. ^5-31036, shall be incorporated in the escape 

tower structural assembly. !Ilie cover assembly shall shield the antenna 
fairing dxiring the launch period. 



MAC 291 CM ItOMAWMI 



O^j, 20 January 196?. MME^,^£^ ,^Oi iL 

REVISED ST. LOUIS. MISSOUU REPORT ^603blif 

REVISB) aOfJ^mt^UtMrnm MOoa Mercury Capsule 



3.6 HEA.T AM) mCROMEIEORIIE SHTKT.T^IHG 

3.6.1 FOREBOIg HEAT PROTECTION - The capsule shall be protected by a 
dish*- shaped heat sink which shall form the forward surface 

(forebody) of the capsvile. The heat slnk^ In accordance with MAC Drawing No. 
^3-^32031, shall be fabricated of hot pressed sintered 9C7 grade berylUum^ 
forged to its final size of 7^.5 inch diameter with an 80 inch spherical 
radius. The beryllium heat sink shall also provide protection from loads 
Imposed by launching acceleratioas, retrograde rocket firing, parachute 
deployment and dynamic air loads. Design consideration has been given to 
ifttn^ing loads on the heat sink to instire that the pressure vessel is not 
punctured on water landings. The heat sink shall be attached to the capsule 
conical structural assembly (afterbody) by a titanium attach ring. The 
attach ring, riveted to the capsule structure assembly, shall contain U& 
elongated holes (to allow for thermal expansion) to mate with bolt holes 
spaced about the zlm of the heat sink. 

3.6.2 AFTERBODY HEftI PROTECTION - Afterbody heat protection shall con- 
sist of a radiation shield on the outside surface with insula- 
tion between this shield and the primary stractture. ^e radiation shield 
shall be ccnqposed of numerous individual corrugated shingles attached by 
bolts through oversize holes to aUow thezmal expansion while ronainlng within 
acceptable flutter limits. Shingle material shall be Rene' ^1 on the antenna 
fairing and conical afterbody section and aluminum on the cylindrical 
recovery ccorparlment. Biermal leakage to the inner structxire shall be 
minimized by using insulation between the outer and Inner skin. This 
insulation shall also serve to attenuate the external noise level* 

3.6.3 MICROMETBORITE PROTECTION - Protection of the underlying 
pressure capsule against impacts from micrometeorites shall be 

provided by the use of the corrugated shingles specified above. 



MAC24I CM 00 MAN Ml 



ST. louis, Missoun REPORT ^§92:2k. 



REVISED 



REVISED > WyWPlg ifci3fcgMBBF iunnR Mercury Capsule 



3.7 BOOSTER ADAPTER - NASA shall be responsible for matching 

Mercury Capsule No. l^f to a modified Little Joe No. 5A booster. 
!Qie capsule shall be used in a manner which requires a minimum of modification 
to tbe booster system. Ihe booster adapter assesnbly for mating Mercury 
Capsule No. llf to the Little Joe No. ^A booster shall be of conventional 
semlmonocoque alumlnrmi^ steel and magnesixai construction. This shall consist 
of a basic Little Joe adapter and an adapter extension asseaiibly, NASA No. 
803305, irtiich shall provide the additional length required to accommodate the 
retropackage. The adapter extension assembly shall consist of a machined 
structural Arame utilizing (l) a special Atlas adapter ring^ MAC Drawing No. 
^^5*33501, which shaU be fabricated and installed by NASA; (2) a capsxile 
match ring, NASA Ho. 803297; (3) a top adapter ring, NASA No. LC 803295; 
{k) a bottom adapter ring, NASA No. LC 803296; (5) a pressxure plate, NASA No. 
LE 802861, which shall be held in place by (3) and (^), and with an aluminum 
sheet metal skin of sufficient thickness to withstand the required loads. 
NASA shall furnish the adapter extension assembly to MAC for incorporation 
of the necessary wiring and rework. The adapter extension assembly shall 
then be shipped to the la;mch site with the capsule, assembled, and then the 
capsule and adapter extension assembly shall be attached to the basic adapter 
on the Little Joe No. 5A booster. MAC shall be responsible for the design 
and manufacture of a clamp ring assenhly which shall be used to attach the 
capsule to the adapter assembly. The clamp ring assembly shall consist of 
three (3) segpiented sections joined by three (3) explosive tension bolts. 
Two (2) of the explosive bolts can be initiated electrically f3rom either end 
by a dual electric system. The third explosive bolt may be initiated 
electrically from one (1) end only on Capsule No. 1^. 



MACaSI CM (10MA(IM» 



REVISED ST. LOUIS, MI SSOIIM REPORT 66O3-IA 

REVISED ilffWWlliaS'lUA^ annPi Mercury Capsule 



3»8 CREW STATION - The crew station in Capsule No. ik shall be 

basically identical to manned capsule crew stations, except for 
tbe special instrumentation provided for the mission requirements as defined 
in Para. 1.1.1 herein. Equipnent for astronaut support such as the support 
coxich, restraint system, hand controller, emergency handle, food and water, 
and waste handling shall not be required in this capsule. 

3-8.1 CONSOLES 

3.3.1.1 RIGET-'HAMD CONSOIiE - Qie right-hand console in accordance with 
MAC Drawing No. 45'-8l002 shall contain no controls for tbe 

mission of Capsule No. 1^ as defined in Para. 1.1.1 herein. (Qie rlght-^hand 
console shall be finished In li£^t blue space capsule coating Z&-266 com-* 
patlble with the life support color code as applied to the main instrument 
panel. 

3.8.1.2 LEFT-HAND CONSOLE - The left-hand console in accordance with 
MAC Drawing No. 45-81110 shall consist of two panels; the inner 

panel adjoining the Instrument panel, and the outer panel. Only those 
instruments necessary for the mission of Capsule No. ik fi>*Aii be installed. 
!Qie left-hand console Inner panel shall be finished in light brown space 
capsxale coating XA.-263 and the outer panel shall be finished in dark brown 
space capsule coating XA-264, except for the pressurization controls area 
^A^Qt shall be finished in li^t brown XA-263. 

3.8.2 IHSTRUMENIATIOW AND DISPIAIB - A main instrument panel assembly 

in accordance with MAC Drawing No. ^5-81100 shall be provided. 
The izistrument panel shall be supported from capsule structure on the upper 
left and by the periscope housing (see Para. 3.16.1). The instruioent panel 
shall extend aroiand both sides and the top edge of the periscope such that 
ihe scope display shall appear in the lower center of the instrument display, 
dls installation shall provide an optical reference point ^Ich falls at 
the Intersection of Station FZI35.59 and TZ^.TSO. All instnsaents shall 
have ^dilte indices on blade background. The instrument panel shall be coded 
to Indicate specific functional areas by color. Ibese shall be as follows: 

JAiHUTiaN SPACE GAPSDLB COATING 

Life Support Light Blue XA-266 

Electrical Light Green XA-26T 

Badlo Dark Green XA-269 

Warning Medium Green XA-268 

Bli^t Light Grey XA-^5 

Altitude and Descent Tan XA-262 
Fuel Indication ^ Dark Brown XA-26i<. 



MAC 231 CM (lOMARSa* 



nATc 20 January 

REVISED 

REVISED 



^ M^DONNEU.^ ^ 



^otd&m PAGE 



20 



ST. LOUIS. Missoun 



REPORT 



6603-1^ 



MQDPL MercuiT Capsule 



3. 8*2 



mSTRUMENIATION AMD DISPIAYS - (Continued) 



Basic instrumentation, depicting transraitting and/or recording 
methods for obtaining measurements defined below are as illustrated in 
Figure 6, Page ij-O. Instrumentation specified below shall be provided by the 
contractor. 



(a) Vehicle Measurements 

Time Reference (See Para- 
graph 3*8«3) 

Visxxal Attitude Reference 
(See Paragraph 3.l6,l) 

(b) Operational Measurements 
A.C, Voltage 

D.C. Voltage 
B.C. Current 



Panel 
Indication 



Recording Method 
(See Figure 6) 



X 



X 



X 



X 



3.3-3 



TIME REFEEIMCE IIIDICA.TEQH - An interim satellite cloci: in 



accordance with MAC Drawing No. 45-81059 shall be provided as 
specified in Appendix I-C, Item 2 herein. This clock a spring driven chronom- 
eter, shall indicate time of day and elapsed time (seconds) from launch. 
The retrograde timing mechanism shall have an adjustable time delay, 250-330 
seconds, which shall be preset to the desired time of retrograde prior to 
launch. !Itie retrograde timing mechanism shall, upon run out of the time 
delay, provide a retrograde fire signal. Signals of elapsed time from lift- 
off shall be transmitted to telemetry as indicated in Figure 6, Page ^, 
herein. Elapsed time (seconds) from launch shall be displayed on a Veeder- 
Root counter. Ttxis clock shall be installed in Mercury Capsule No. lU in 
lieu of the satellite clock, MAC Drawing No. 1^5-81710 • 



3-8.1^ 



3.8.5 



ANGULAR RATE AND ATTITODE INDICATOR 

NoTTTn 



Not provided on Capsule 



SEQUENCE SYSTEM AND OVERRIDE CONTROLS - lie sequence system 
shall consist of engraved nameplate and telelight sequence 
lights with adjacent manually opera1:ed override controls. This system shall 
indicate functional sequence of events by illumination of a green light for 
normal sequential operation or, after a time delay, by a red light indicating 
a malfunction and need for siib sequent override action. After corrective 



MAC 231 CM <tO MAM 9»l 



n^TK 20 January I961 

KPflSED. 

REVISB3 



MCDONNELL 



^m^m- Lc^otd&7t 



PAGE 



21 



St. LOWS, MISSOUU 



REPORT 



66Q^^lk 



unngL Mercury Capsule 



3.8.5 



SEQDMCE SIGSTEM AHD OVERRIDE COHTRCSLS - (Continued) 



action has been taken^ the telelight shall lllumlnAte green as in noimal 
sequential operation. In order of chronology, the following shall appear on 
the left-hand console: 



HOMECTCIATURE 

Launch Control 
Jett Otower 
Sep. Capsule 
Retro Seq« 
Retro Att. 
Fire Retro. 
Jett Retro. 
Retract Scope 
.05g 
Brogue 
Snorkel 
Main 
Reserve 
Tianding Bag 
Rescue 



OVERRIDE CONTROL 



Toggle Switch 



Push Button 
Toggle Switch 
Push Button 
Push Button 
Toggle Switch 
Push Button 
Push Button 



Toggle Switch 
Toggle Switch 



SWITCH NO. 

P-1 

P-3 
P.4 
P.6 
P-8 

P-7 
P-10 

P-20 
P-11 
P-12 

P-13 
P-lifr 
P-25 
P-15 



PRESENTATION 

Engraved Nameplate 

Telelight 

Telell£^t 

Telelight 

Telenet 

Telelight 

Telelight 

Telelight 

Telelight 

Engraved Nazoeplate 

Engraved Nameplate 

Telenet 

Engraved Nameplate 

Telelight 

Teleli^t 



Switch nimbers represent manual override controls and corres- 
pond to those indicated in the sequential schematic. Figure h, Page 30L 

Bae guarded push button controls shall provide override control 
by a dual electrical system for each function desi^, . Led. The toggle 
switches shall function in a left-right direction and their nomenclatiore shall 
be as follows (in order of sequence and left-iright readings): 



Launch Control 
Retro Att. 
Retract Scope 
Landing Bag 
Rescue 



"Ready-off" 
"Auto-Bypass" 
"Auto-Man. " 
"Auto-Man. " 
"Auto-Man." 



The telelight ass«ablies in accordance with MAC Drawing No. ^5-79720, shall 
be rectangular in shape and shall consist of red and green light assemblies, 
nomenclature caps and retention clips. Legends shall be direct reading, 
engraved in black on ftrosted glass plate ncmenclatxire caps' and shall be 
readable when the li^ts are de-energized. Colors shall be in accordance 
with FED-STD-3. Brightness of the ligihts shall be as required by MIL-STD-^11 
for 2^ volts application. 



MAC 231 CM (to MAR 99% 



ftATB 20 jBuwary I96I 

REVISE) 

REVISED 



MCDONNELL 



37'^i0fa^ i.>o^old£cn 



PAGE 



22 



ST. LOUIS, MlSSOWl 



REPORT 



6603-lU 



unna Mereury Capsule 



3.8.5 



SEQUENCE SYSTEM ATTO OVERRIDE COHTROLS - (Continued) 



The engraved nameplate shall be constructed of aluminum material 
and shall simulate the telelight assemblies in fozm and size. Nomenclature 
on the nameplate shall be vhite on a black background. 



3.8.6 



3.8.7 



DEAD RECKONING EARTH PATH IMDICATIOIT - Not provided on Capsule 
No. V^, 



SWITCHES AND HANDLES - !Ilie following switches and handles with 
their respective nomenclatures and functions shall be located 
on -me instrument panel and left-hand console, as indicated. IHiis tabulation 
shall be exclusive of sequence system override controls as specified in 
Para* 3.8.5. 

NQMENCLATORE 



OJype 


Actuation 


Function 


Location 


Toggle Switch 


Qn-Off 


Hi-Pwr. Telemetry 
(Low Frequency) 


Left-land 
Console 


Toggle Switch 


ASCS Only • 
Auto-Ptos Only 


Standby Inverter (P-l8) 




Toggle Switch 


anerg-Noxm 


Aixdio Bujs 




Toggle Switch 


Bypeiss-Uoxm - 
Pwr. Off 


Ammeter 




Toggle Switch 


ASCS*-Fans 


A.C. Volts 




Toggle Switch 


Ifon-Auto 


Standby Battery 


Main 


Toggle Switch 


Standby-Noxm 


Isolated Battery 


Instrument 


Toggle Switch* 


ASCS Off -Norm 


Electric Power 


Panel 


Toggle Switch 


Dim-Bright 


Warning Lights 




Toggle Switch 


R/T-Noim 


UHt' DP (P-21) 




Toggle Switch 


Lo Pvr-HI Pwr 


ITHF Select (P-22) 




Toggle Switch 


HP-UHF-Off 


Tranfimit 




Toggle Switch 


Gmd Ccmd - 
Cont. 


Beacon 





* Installed hut inoperative 



MAC 231 CM <IOMARS«) 



„,„ ao O^nusr. X?61 MCDONNELL ^ ^^^^^ P>o. . ^ 

REVISED ST. LOWS. MISSOUM REPORT ^^Q3-l^ 

REVISED ftTrTfTDTOTiV^iBi AAnnpi Mercury Capsule 



3-8.8 SWITCH FUSES - Switch fuses shall be provided for "ifl^i^aT reset 

of interrupted circuits. No special visual systems for indica- 
tion of an interrupted circuit shall be provided. Switch fuses shall be 
located on the main instrument panel and on a switch fuse panel located to 
the outer panel of the left-hand console. 

The following switch fuses shall be located on the extreme 
ri^t of the main instrument panel: 

Suit Fan Envir. Contl 

Retro Jett Retro Man. 

Programmer Spare 

!Qie following switch fuses shall be located on the switch fuse 
panel as follows: 

Spare 

Boer Cap Sep Contl 

Boer Escape Rckt 

Otower Sep Contl 

Bner Tbwer Sep 

Eater Sower Jett 

Bner Fosgrd 

Spare 

No. 1 Retro Rckt 

No. 2 Retro Rckt 

No. 3 Retro Rckt 

Baer Retro Seq 

Bner Retro Jett 

ASCS .05g 

Bner .O^g 

Bner Drogue Deploy 

Bner Main Deploy 

Reserve Deploy 

Bner Reserve Deploy 

Bner Tinnding Bag 

Bner Rescue Aids 

Periscope 

Ant Switch 

Ccmd Rcvr A 

Low Tel Snit 

3*8.9 LIGHTIHG - Not provided on Capsule No. ik. 



MAC 231 CM (lOMMKSal 



I 




\^% 



i I I 




I 



PA1E 20J^uarrl?6l MWMm.^ ^ CyM^iSoK PA« !L 

REVISED ST. LOUI S. MISSOUM REPORT §§23zl^ 

REVISED JiftWiP§llSffSE03B55? MODH. Mercxary Cax>sule 



3-9 CAPSULE EHVIROHMEtraAL CONTROL 

3 •9-1 EKYIROMMEMTAL CQMTROL SYSTEM - A functional environmental con- 
trol systoa shall not te provided in Capsule No. li<.. Die 
environmental control system components, as specified in Appendix I-C, Itea 8, 
shall provide the following: 

a. Cooling, pre- launch 

b. Cabin pressvire relief 

c. Valve, post landing outflow 

During the prelaunch phase, Preon 12)^ refrigerant shall be 
introduced into the cabin heat exchanger via the capsule umbilical for 
cooling eqxiipment within the cabin. The cabin equipment fan, energized as 
power is applied to the capsiiLe, shall circulate air around equipment until 
re-entry, at 20,000 feet altitude, when it shall be de-energized automatically 
and the snorkel valves shall open as depicted on the sequential schematic. 
Figure h^ Page30 . During ascent, the cabin differential valve shall utilize 
initial cabin oxygen content to maintain a cabin pressiore which is 5.5 psi 
above ambient at altitudes above 13,000 feet. 

3*10 STftBTT,T7ATI0N CaNOBOL SUBSYSTEM - No stabilization control 
systems shall be provided in Capsule No. l4. 

3-10.1 AUTOMATIC STABILIZATION AND CONTROL SYSTEM - Not provided 
in Capsule No. 14. 

3.10.2 RATE STABILIZATION AND CONTROL SYSTEM - Not provided in 
Capsule No. 14. 

3-10.3 HORIZON SCANNER - Not provided in Capsule No. l4. 

3*10. i^ REACTION COHTOQL SYSTEM - Not provided in Capsule No. l4. 



MAC2af CM UOMAIIMI 



DATE SQ Jaaviarv 1961 Mlkfilili^^,-^^^ Lotfiotdiiort 




REVISH) ST. LOWS, MISSOUM 

REVISH) 



^ K7 :^ l^*^:NIV'*f 



PAGE 


26 


REPORT 


66o^-llt 


MODEL 


Mercury Capsule 



3«11 RETOOGRADE ROCKET SYSTEM 

3«11»1 DESCRIPTION - The retrograde rocket system for Mercury Capsiole 
No. 14/LJ-5A shall consist of three (3) expended Biiokol Model 
TE*3l6 solid propellant rockets, with svifficient simulated propellant added 
to serve as ballast to hold as close as possible to the true C.G. of 
Mercury Capsule No. l4. Rocket design details and testing fiV>fli i be as 
described in MAC Drawing No. i*-5-50TOO, (see Appendix I-C, Itaa 1, herein). 

3»11«2 INSTALLATION - The retrograde rocket assembly shall be mounted 

in a structural assesibly in accordance with MAC Drawing No* 
^5-50002. OSais shall consist of a structural frame assembly encased within 
an instzlated aluminum housing which g>'fti i be secured external to the heat 
sink by retaining straps. Ihe retaining straps, in accordance with MAC 
Drawing No. ^^5 -72030, shall be attached to the capsxie by retention fittings 
in accordance with MAC Drawing No. i<-5- 32086, which shall remain engaged only 
so long as tension exists in the straps and to the rocket structural 
assembly by a centrally located explosive bolt in accordance with MAC 
Drawing No. 1^.5 -7270^4-. For capsule shipaent, an inert explosive bolt shall 
be provided, but prior to capsule launching, a "live" explosive bolt shall 
be installed. Jettison of the retrograde rocket a^senbly shall be effected 
by release of the retaining straps by firing the explosive ejector bolt, 
removing tension from the retaining straps, and permitting a compression 
spring jettison assembly, in accordance with MAC Drawing No. ^^5-50013, to 
thrust the retrograde assembly from the capsule. Initiation of the ejector 
bolt sha ll be through the abort firing circuitry (see Figure ^, Page 30). 

3-ll»3 POSICgtADE ROCKET SYSTEM - llhe posigrade rocket system for 

Mercury Capsule No. 1^ shall consist of three (3) eacpended 
Atlantic Research Corporation solid propellant rockets. Sufficient simulated 
propellant shall be added to serve as ballast to hold as close as possible 
to the true CO. of Mercury Capsule No. l4. The dummy posigrade rockets 
shall be symmetrically mounted in the retrograde rocket assembly housing 
between the dummy retrograde rockets. 



MAC 2*1 CM <I0 MAII Ml 




REVISB) ST. LOWS, MISSOUH. 

REVISB) 



PACE 


27 


PPPnBT 


660^-llv 


Monw Mercury Capsule 



3 •12 ESCAPE SYSTEM - An active escape syston shall be provided as 

part of the capsule. This system shall be capable of function- 
ing up to tower separation should it become necessary to abort either prior 
to or later than the time at "which normal abort would occur during the 
Little Joe No, 5A mission* Escape sequence prior to release of the active 
escape system for either the normal Little Joe No, 5A mission or any other 
aborted mission shall be as specified in Paragraph 3.12.5 . 

3 •12.1 DESCRIPTION - The escape system shall include a pylon fi'ame- 
work assembly in accordance with MAC Drawing i|-5-31001, which 
shall support an escape rocket installation in accordance with MAC Drawing 
Ho. 45-51001. Die escape rocket installation shall consist of a structural 
assembly in accordance with MAC Drawing No. 45-51002, an escape rocket in 
accordance with MAC Drawing No. 45-51700, a pylon jettison rocket in 
accordance with MAC Drawing No. 45-51701, an aerodynamic spike in accord- 
ance with MAC Drawing No. ^5-51010, and ballast assembly in accordance with 
MAC Drawing No. 45-510IO. The pylon assembly shall be a tower structure 
consisting of three (3) longitudinal members of tubular steel construction 
diagonally braced and g^**^**"! incorporate an antenna cover asseinbly for 
shielding the antenna fairing. The pylon shall be attached to the capsule 
cylindrical recovery comparhaent by a clamp ring eissembly. A k^^ aerodynamic 
fairing shall be installed over the pylon clamp ring to reduce the pylon 
ballast weight and to facilitate greater aerodynamic stability of the 
capsule up to tower separation. The clamp ring assembly, in accoixLance with 
MAC Drawing No. 45-72040, shall consist of three (3) segmented sections 
each joined by explosive bolts in accordance with MAC Drawing No. ^5-72702. 
Two of the explosive bolts shall be initiated electrically from either end 
by a dual electrical system and the third bolt shall be electrically 
initiated from one end only. Initiation of the clamp ring separation explo- 
sive bolts shall be as described in Paragraph 3. 12.5. 

3 •12* 2 SSCAPE ROCKET - The escape rocket, in accordance with MAC 

Drawing No. 45-5170O, shall be sxipported by the pylon structure 
and the aerodynamic spike and ballast assembly shall be secured to the 
escape rocket structural assembly. Ihe escape rocket shall consist of a 
solid pxtjpellant rocket motor with three (3) nozsJLes canted nineteen (I9) 
degrees frcm. the longitudinal axis of the rocket case and an electrically 
actuated igniter. Dae nominal action time for the escape rocket shall be 
1.39 seconds with an average resultant thrust of 52,000 pounds at its 
centerline. Nominal thrust impulse rating of this rocket shall be 56,500 
pound-seconds, under conditions specified in MAC Drawing No. ^4^5-51700. 

3*12.3 PYLON JESCnsON ROCKET - Die pylon jettison rocket in accord- 
ance with MAC Drawing No. i|-5-51701, shall be supported by the 
escape rocket structural assembly. This rocket shall be mounted on the 
escape rocket longitudinal axis among ^e canted nozzles. The pylon jettison 
rocket sha ll consist of a solid propellent rocket motor, and electrically 



MAC 231 CM (lOMAIIS«l 



REVISED ST, LOW S, iHUSSOIIII «PORT 6603^ 

REVISB) JPiBHRf^^^NXfjIi)^ Mnna Mercury Capsule 



3-12.3 FELON JETTISON ROCKET - (Continued) 

actuated igniter utilizing a tri-nozzle exhaust arrangement. The nominal 
action time for this rocket shall be 1.6 seconds with a maacimum resultant 
vacuum thrust of 765 pounds and total impxilse of 111^5 pound- seconds, under 
conditions specified in MAC Drawing No. 45-517OI. 

3«12.^ ESCAPE STGSTEM PERFORMANCE - The escape system during an escape 

ftrcm the ground launching pad shall propel the capsule to an 
altitude of approximately 2200 feet. Determination of the nominal escape 
rocket thrust eccentricity shall be the result of rational analysis which 
win attain a reasonable compronlse between adequate capsule-booster 
separation distance and tolerable structural lateral load factor character- 
istics. The analysis shall consider effects such as: 

a. Capsule abort conditions as a result of booster malfunction. 

b. Booster flight characteristics subsequent to capsule- 
adapter separation. 

c. Capsule escape rocket thrust eccentricity tolerance. 

The determination of booster flight conditions leading to the 
initiation of 1±ie abort maneuver and following capsiole separation shall not 
be the responsibility of the capsule contractor. 

3«12.5 ESCAPE SYSTEM SEQUENCE - The escape system sequence for the 

Little Joe No. 5A normal aborted mission or any other aborted 
mission shall be as specified in the following paragraphs. 

3.12.5*! NORMAL MISSION - The normal mission for Little Joe No. 5A shall 
be an aborted mission to evaluate the escape system. The abort 
ccomazid shall be initiated by NASA supplied 3^.6 second time delay relay. 
OSie NASA supplied time delay relay shall be located in the adapter section 
and shall be NASA installed. Upon receipt of an abort signal from the 3^.6 
second time delay relay, the capsule "Mayday" light shall be illuminated, 
a si03al sent to the maximum altitude sensor (Time Versus ^m^^ Computer) and 
the capsule adapter clamp ring explosive bolts detonated. The time delay 
( AT) for tower jettison with relation to time of abort (Ta) after time 
zero shall be as follows: 

At, sec a 0.5 Tj^ + 8.0 5 T^ 

A capsule adapter separation sensor shall detect separation of the adapter 
clamp ring and initiate firing of the escape rocket ^vdiich shall propel the 
capsule from the path of the missile. (See Para. 3*I2.4). The capsule 
adapter ring separation sensor shall also initiate firing of the retrogrades 



MACaai CM (IOM«J»M» 



0.^ ^ .7a.w i9$i MCDONNELL ^ ^^^^^^ „„ ^ 

REVISED . ST. lows, MISSOUM _ REPORT 6603.1!^ 

REVISED ^WfPfJjjBSWOT^ MOOa Mercury Capsule 



3.12.5-1 NORMAL MISSION - (Continued) 

rocket assembly separation bolts and shall close a relay to allow a signal 
to pass from the zna^dmum altitude sensor to the tower separation bolts. Ibis 
relay shall prevent _f iring of the tower separation bolts prior to the firing 
of the escape rocket. Hxe maximum altittade sensor shall delay firing of the 
explosive bolts in the tower separation ring until a safe dynamic pressure 
is reached. A tower ring separation sensor shall detect separation and 
initiate firing of the tower jettison rocket which shall separate the tower 
frazi the capsule. !Ihe tower separation sensor shall detect tower separation 
and shall axm the larnilng sequence system, which shall commence after a 
TnlnlTnxm time delay of two (2) seconds. 

3«12.5»1«1 TIME SEQUENCE - The programmed time sequence for the Little 

Joe No. 5A normal mission shall be as follows (Reference 
Figure h^ Page 30 ) : 

EVENT TIME LAPSE (APERQX.) 

a. Booster firing T^ 

b» Maximim altitude sensor activated T^ + 3h.3 sec. 
capsule adapter bolts initiation^ 
and retrograde assembly separation 
initiation 

c. Tower sepsuration bolts initiation Tq + 59*75 sec. 

d« 10,000 feet barostat actuated T^ + I78 sec. 

e. Dual inertia switch activated T^ + ^99 sec. 
(at impact) 

3.12.5«2 ABORTED MISSIONS - For Little Joe No. 5A an aborted mission 

shall be defined as a mission which has the abort signal 
initiated by some source other than the 3^-6 second time delay relay. 
Abort indication shall be provided by a red '"Mayday" light on the instru- 
ment panel which shall indicate an abort. 

3.12.5-2.1 ABORT INITIATION - An abort shall be initiated by application 

of a 2a volt sigial. to the abort jimction in the escape system 
electrical network. U^on receipt of a signal^ the 28 volt source shall be 
instantly "locked- in" at this junction and shall provide the necessary power 
source to initiate the abort sequence, consistent with the mode in which 
the abort maneuver is necessary. 

3.12.5.3 ESCAPE SEQUENCE OFF THE PAD AHD PRIOR TO TOWER SEPARATION - 
Not provided on Mercury Capsule No. 14. 



MAC 291 CM (10 MAN Ml 



L 



It 



I 



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O 



O 
u 

< 

z 
o 

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3 



3 
to 

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.11 



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55 5 5555 [fSi' 







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§ g I 






REVISED ST. LOWS, MUSSOUH REPORT 6603-1^ 

REVISH) jg|if«L!lB^]|tiHlil!l-gP MnnPi Mercury Capsule 



3*13 ELECmiCAL POWER SUPPLY SYSTEM - The electrical power supply 

system shall consist of 6 batteries^ in accordaace with MAC 
Drawing No. ^5-7970T> vhich comprise the main^ standby, and isolated power 
supplies. Inverters shall be used for conversion of D.C. power to A.C. 
power. All batteries shall have individual diode reverse current protection 
for prevention of unnecessary power consumption because of a weak or faulty 
battery. Each battery shall, be sealed at sea level pressure to withstand 
a pressure of Ik. J psi both internally and externally, and shall have a 
pressure relief valve for maintaining internal pressure between psi and 
1^.7 pel as required. The batteries shall be vented for release of gas 
only with vent lines passing througjh the large pressure bulkhead and 
terminating in the capsule skin Jixst aft of the bulkhead such that the gas 
vents overboard. Voltage monitoring shall be provided by the volianeters 
located on the main instrument panel. Electrical loads shall be categorized 
as essential and nonessential and applied through separate busses tlarotxgh 
separate fuse panels. In event of low battery voltage, the nonessential 
bus automatically shall be switched "off". The D.C. power control system 
shall be as depicted in Figures 5a and 5b, Pages 33 and 3^ • 

3.13,1 MAIN POWER SUPPIg - Die main power supply shall consist of 

three (3; 1500 watt/hour silver zinc batteries. (See 
Appendix I-C, Item 3 herein for electrical components). Terminal voltage 
of these batteries shall average approximately 23 volts with a maximisa of 
29*6 volts and a minimum of I8 volts. The main batteries shall be wired 
in parallel with diodes for reverse cinrrent protection. 

The main batteries Rhall be capable of providing power require- 
ments for the mission as defined in Para. 1.1.1 herein. Monitoring of each 
batteiy shall be provided by the voltmeter located in the main instrument 
panel by indication of available voltage. One battery g>^ft'^i provide power 
for the special instrumentation required for the LJ*»5A mission. 

3 •13*2 SIftHDBY POWER - The standby power supply shall consist of two 

t2) 1500 watt/hour silver zinc batteries. Bxe standby batteries 
shall have capacity sufficient to provide power to capsule equipment for the 
dtiratlon of the fll^t as we3J. as a 5.5 hoxir requirement for post landing 
conqponents. Selection of automatic operation shall be made by a switch 
provided on the main instrument panel (see Para. 3.8.8) prior to launch. 
Selection of automatic mode shall insert standby power into the main power 
sxzpply system should a failure occur. A standby B.C. warning light shall 
beccme illuminated at this time and all nonessential loads deprived of 
power. The standby system shall automatically continue to s\apply power to 
essential loads. 



MACaSlCM no MAM Ml 



REVISED ST. LOUIS, MlSSOUm 



REVISED 



PArtP 


32 


PFPOPT 


6603-liv 


MnnPi Mercury Capsule 



3.13.2.1 ISOLATED POWER - The isolated power supply shall consist of 

one (1) 1500 watt/hour silver zinc battery. The isolated 
battery syst«a shall have sufficient capacity to provide power to the pyro- 
technic actuated devices (^ee Para. 3.20) . 

3.13.3 A>C. POWER - A,C. power reqioiresients shall be supplied by con- 
version of D.C. power throiogh utilization of one (l) I50 VA 
main static inverter and one (l) 250 VA standby static inverter > in accord- 
ance with MAC Drawing No. ^5-79709. 

!Ilie 250 VA inverter shall be mounted on the outboard side of 
Sta. 1x21.625 above Sta. YO.OO and the I50 VA inverter shall be mounted on 
the outboard side of Sta. LX12.00 below Sta. YO.OO. The A.C. systea shall 
provide sufficient power for the mission as defined in Paragraph 1.1.1* 
herein. 

3.13^^ EtECTElICAL COMECTIOHS - Die electrical system shall be pro- 
tected against corrosive atmosphere and shorting by floating 
debris. Design of the electrical system shall be such that there shall be 
no exposed electrical connections within the capsule. 

3-13.^.1 IMBILICAL COMlgECTICTTS - In order to maintain a fully charged 

condition on the batteries and to provide power for groimd 
testing of variotis systans within the capsxile, external power shall be 
supplied to the capsule prior to launching thi^ugh an umbilical cable and 
disconnect assembly, MAC Dra;rtng No. ^5-79723 • This cable shall be attached 
to the capsule mating receptacle through the open periscope door in accord- 
ance with MAC Drawing Ho. ^5-79096. The umbilical coupling device shall 
afford a secure and a positive connection at the capsule, capable of being 
released both electrically by a solenoid release mechanism and manually by 
a lanyard release as specified on MAC Drawing No. ^5-79723 • It shall be 
the function of the umbilical connection to provide for the transfer of Freon 
Hk to the capsule at such a rate and manner as specified on MAC Drawing No. 
^5-79723- 



MAC 231 CM (10 MAR SSI 



L 



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nAn 20 January 

REVISED ST. LOWS, MISSOUM 



REVISED 



■-*rjS.^.^_iJ> 



PArtF 


^5 


BPPDBT 


6603-U 


AAODElflercury_Cajas.ule 



3, 1^4- COtMUHICATIONS SYSTEM - Coiiimx:uii cations provided aboard 

Merciory Capsiile No. ik shall consist of high and low frequency 
telemetry transmitters^ their power supplies and antenna, and a C-Band radar 
beacon system. Data shall be telemetered to the ^^Tallops Island ground station 
to provide necessary real time information concerning the capsiile. Telemetry 
sha]] afford a back-up in the event onboard data are not retrieved. Relia- 
bility Fihall be obtained through the use of two independent telemetry 
systens. Both telaaetry units shall be energized through the telemetry 
power supplies at umbilical separation. The telemetry transmitters shall 
operate continuously through the biconlcal antenna until antenna fairing 
separation at which time a coaxial switch shall transfer the imits to the 
descent antenna. 

3-l^»l LOW roSQUMCY lELEMETOY TRANSMITTER - The low frequency 

telemetry transmitter shall operate on 225*7 megacycles with 
a transmitted power output of 3.3 watts. This unit shall transmit scientific 
infonnation by means of 7 IRIG standard PM subcarriers, one containing PAM 
modulation (10. 5 kc subcarrier) which shall, provide 90 data samples, each 
measured 1-1/^ times per second. This unit shall satisfactorily transmit 
any standard TRIG sxibcaxTier channel up to 20 kc with 20 kc deviation and 
shall be capable of U-1/2 hours continuous operation. 

3. 1^4.. 2 HIGH JREQUENCY TEILEMETRY IRMSMITTER - The high frequency 
telemetry transmitter shall operate continuously on 259*7 
megacycles with a transmitted power output of 3.3 watts. This unit shall 
have the capability of transmitting a power output of 0.6 watts by a simple 
ground modification required for conversion to the lower power. This unit 
shall transmit scientific and angular rate information by means of 7 IRIG 
standard JM subcarriers, one containing PAM modulation (10. 5 kc subcarrier) 
which shall provide 90 data samples each measured 1-1/^ times per second. 
This unit shall satisfactorily transmit any standard IRIG subcarrier 
channel up to 20 kc with 20 kc deviation, ^en transmitting at 3*3 '^'atts, 
the high frequency telaaetry transmitter shall be capable of ^1/2 hours 
continiaous operation. When transmitting at 0.6 watts power output, this 
unit shall be capable of 28 hours continuous operation* 

3.1^^.3 TOrr.T^iffilER POWER SUPPLY - Two (2) identical transistorized 

power supplies shall be provided, one for each transmitter. 
Bie power supplies shall operate from the capsule D.C. power supply. 

3.li4'.l4- TRT.TTMETOY LINE FILTER - A telemetry line filter shall be pro- 
vided. TSfie line filter shall reduce conducted RF energy 
being fed directly back fircm the high frequency telaaetry transmitter into 
the oapsule wiring to a level compatible with satisfactory systaa operation. 



MAC Zai CM <tO MAK 99t 



HATP 20 January I96I 

REVISH) 

REVISB) 



MCDONNELL 



^^^y^uie^um- L4^otd&nt 



PAGE 



36 



ST. LOWS, Missoun 



REPORT 



6603-1^ 



unna Mercury Capsule 



3* 1^*5 C*BAHD BEACON - The C-Band radar tracking beacon ?>?a1 1 be com- 
patible with the FPS-I6 radar system. The C-Band beacon trans- 
ponder shall consist of a transistorized receiver operating on a 5W0.Q mega- 
cycle frequency and a transistorized transmitter ( except- ^or its magnetron) 
operating on a 5555 •O megacycle frequency. The transponder input shall be 
double pulse coded and shall provide sufficient receiver sensitivity to 
normally attain a range of 805 statute miles (7OO nautical miles) at 
orbital altitude* Power output of ^ this unit shall be 375 watts peak. 

3*14.6 C-BAMD ANTEMHA -^C-Band antenna systea capable of operation 

during all phases of the mission shall be provided* ie C-Band 
beacon shall remain enei'j^zed until 10 minutes after impact through a time 
delay energized by tlierlanding system dual inertia switch as indicated on 
the sequential schematic. Figure \f Page 30. IMS antenna system shall con- 
sist of three flush helices to provide omnidirectional coverage, with a power 
divider and matched cabling from the power divider to the antenna. The 
C-Band antenna shall be externally located in a band around the capsule 
conical section near the jxmction of the cylindrical recovery compartment. 

3«l4'7 BICOHICAL MTEMTA - The biconical antenna shall operate 

throu^-the re-entry phase of the mission* OSiis antenna shall 
be incorporated into the antenna housing, and shall be Jettisoned at 10,000 
feet geometric altitude with the fairing. Through a multiplexing system, 
both telemetry transmitters shall utilize the biconical antenna. 

3.l4.7«l MULTIPLESER - A mviltiplexer shall be provided to permit simul- 
taneous or individual operation of high and low frequency 
telemetry transmitters into the biconical antenna, ^e multiplexer shall be 
compatible with the UHP descent antenna for use after jettison of the 
biconical antenna, dis unit shall be located in the capsule pressurized 
area. 



3.1^.8 



UHF DESCEMT AHTEiMA ARRAY - A wire butterfly type descent 



antenna shall be provided for supplying omnidirectional coverage. 
^is antenna shall pezmit simialtaneous opeifation of both telemetry trans- 
mitters. Qbe descent antenna shall be located on the capsule parachute 
housing structure where it shall be tethered until after main chute deploy- 
ment to prevent possible damage from the chute risers. QMs antenna shall be 
spring loaded and shall be extended into the erect operating position after 
a 16 second time delay from antenna fairing separation by means of a reefing 
cutter which shall sever the tie-down cord upon actxaation. 

3-l^»9 CPtWDHICATIOMS CONIROL PANEL - A communications control panel 

shall be provided in the lower right-hand comer of the 
instrument panel. The control panel shall contain a **Morse code" keying 
button for high frequency telemetry transmission control. 



(101 



DATE 20 January 196; MlfiQMEU^^ p^^^ 2^^ 

" , ST LOWS, MIS SOU W REPORT 6603^ 

^^9SEm^WB^MMB unnin Mercury Caipsule 



REVISED 
REVISED 



3.li|-.10 COAXIAL SWITCHES - One single pole, double throw^ motor-operated 

coaxial switch shall be provided for switching from the biconical 
antenna to the descent antenna upon main parachute deployment at 10,000 feet 
altitude. 

3.1^.11 COAXIAL CABLES AMD COMHECTOIS - Raytheim Type 12-080S, 12-233 

or 12-23^ coaxial cable shall be used for all interconnections 
between the electronic equipment and emtennas. Coaxial connectors shall be 
of the miniature type. 



MAC 231 CM (lOMARSS) 



r>ATP 20 Janiaary I96I 

REVISED 

REVISED 



M^DOMEIL 



*„^y'uie^em' LAfybotd&nt 



ST. LOUIS, MISSOURI 



-4 %^^%^^% \\[ 



PAGE 




38 


REPORT 




6603-14 


Mooa. 


Mercury 


Capsule 



3 -IS RECORDIIJrG EQUIPMENT - Recording equipment meeting the require- 
ments of Specification MIL-E-5272A-1 and MIL-E-5^0B(ASG) shall 
be comprised of eqioipment as specified in the following paragraphs. A satis- 
factory isolation technique shall he employed to avoid crosstalk or inter- 
ference between systems being fed from common pick-ups. Methods of data 
recording within the capsule shall be as noted below, and as depicted in 
Figure 6, Page^O herein. In addition telemetry equipment for transmitting 
data from the capsule to ground stations shall be provided as specified in 
Paragraph 3<.l4. 



3-15.1 
3-15.2 



a. Sape recording of data 

CAMERAS - Cameras shall not be provided on this capsule. 



TAPE BECORDER - A tape recorder in accordance with MAC Drawing 
No. ^5-titi707, shall be provided for permanent data storage. 
Die recorder shall function continuously during a.n phases of the mission 
and for 10 minutes after iiapact. Bie tape recorder shall be compatible 
with the pulse diaration modulation syst«ii, sxibcarrier oscillators (VCO) 
and direct recording mediums. Siis unit shall have seven heads for record- 
ing data at a tape speed of 1-7/8 ips. !fcpe capacity shall be 4800 feet of 
1/2 inch mylar base- tape. A limit switch shall be provided for interrupting 
power to the recorder in event of tape breakage. Recording tracks shall be 
as follows: 



Track No. 2 - Direct Recording 
Gyro Package 



Accelerometer and Rate 



Track No. 5 - Pulse Recording - composite PDM signal ftom 
Commutator/Keyer IMit '"B" (see Figure 6) 

Track No. 6 - Pulse Recording - composite P!EM signal from 
Commutator/Keyer Ifait "A" (see Figure 6) 

3^15 -2.1 COMMUIATED DATA RECORDING - Two EEM/PAM commutator/keyer 

systems, in accordance with MAC Drawing No. 45-88709> shall 
be provided* dese units shall commutate transducer data and shall supply 
P!DM and PAH outputs. Ihe ccmmutator portion of each unit shall signal inputs 
at a rate of 112-1/2 samples per second providing 90 data samples, each 
measured 1-1/4 times per second, producing a signal wave train. The PAM 
wave train output shall be transmitted to the PAM/FEM converter. Die PEM 
output shall be sxipplied to a record amplifier which shall produce a signal 
capable of directly driving a record head in the tape recorder <» The PAM 
output shall be transmitted to groiand station automatic decommutation equip- 
ment. Each unit shall have its own power to provide required voltages « 



MAC 231 CM CIO MAR S«) 



DATE 20 Jaquary 19^1 

REVISED 

REVISED 



M?D0NNEIL 



'^^tc^UL^ Loybi 



^otdHan PACE 



39 



ST. LOUIS, MISSOUIl 



REPORT 



6603-l^ 



AAnna Mercury Capsiile 



3- 15* 3 VOLTAGE COWTROT.T.Kn SUBCARRIER OSCILLATORS - Voltage controlled 

subcarrier oscillators in accordance with MAC Drawing No. 
i*-5-68700 shall be provided. PAM outputs from the commutators and 3 volt 
D.C. shall apply instrumentation data voltages to the subcarrier oscillators. 

3. 15. 3*1 CCMPEHSAUNG OSCILLATORS - A compensating fixed frequency 

oscillator in accordance with MAC No. U5-8870O shall be provided 
for monitoring wow and flutter. This shall be adjusted to operate at 3125 
cps with an adjustable voltage output. 

3 •15* 3*2 iiQiiK AMELUUat - Tvo mixer amplifiers in accordance with MAC 
Drawing No. 45-88700 shall be provided for capsule power con- 
version from 2^ volts D.C* to 6 volts D.C. for use by the subcarrier 
oscillators. IDiese units shall mix and amplify oscillator outputs for the 
tape recorder and telemetry transmitters. 

3.15.^ SPECIAL INSTRUMENTATION - A special instrumentation installa- 

tion, MAC Drawing No. ^5-88510, shall be provided and shall 
include an accelerometer and rate gyro package^ in accordance with MAC 
Drawing No. U5-8887O, to measure the "g" forces and rate of tianbling 
encountered diiring any abnozmal conditions which shall occur dinring the 
mission of Capsule No. l4 as defined herein. The "g" forces and rates of 
tumbling shall be measured in the following ranges: 



Yaw Rate Gyro 
Pitch Rate Gyro 
Roll Rate Gyax) 



+ 100 degrees/sec. 
+ 100 degrees/sec. 
+ 200 degrees/sec. 



Z axis accelerometer + 15g 
Y axis accelerometer + 8g 
X axis accelerometer + 8g 



The instrumentation installation shall be located between RX9»00 and Zll4.8i<- 
on BY8.75. 



MAC 231 CM (10MAI«S«» 



I 




I 



X 



rr 



t 



' ±XX X X 







XXX 



I 



in 



Xjtz 





) 

n 


•s 


» 


IS 




r 




IJ 



^3 n 










lli 



E 



119 



I 



!I! 



!ii 



ill 



ti 



n 



T till 



1 — I — I — r 



REVISED S T . U HilS. MISSOUM REPORT ^§2>}^ 

REVISB) JW^^^ H^^FRa^lF MODEL Mercury Capsule 



3»l6 NAVIGAnOHAL AIDS - Navigational aids such as a chartboard, 

maps, hand computer and tables, nonnally provided for astronaut 
m a n ual navigational procedures shall not be provided in Capsule EIo. Ik with 
the exception of the periscope as described below. (Bais periscope was 
previously utilized in Mercury Capsule No. 1). 

3*lo*l PERISCOPE - An optical periscope, in accordance with MAC 

Drawing No. ^^5-86701, shall be installed, (see Appendix I-A, 
Item g herein). This unit shall be located so as to partially support uhe 
instrument panel (see Paragraph 3.8.9) such that its display appears in the 
lower center of the instnment panel. Dais installation shall provide an 
optical reference point at EZ 135*59^ TT 5»780 and XO.OO station lines, 
based upon an astronaut's eye reference point at 5X 118.20, TY 22.82 and 
RX 1.28. Bie periscope shall provide an 8 inch diameter circular display 
with the image plane inclination at approximately ^5 degrees from the YO.GO 
axis. Ihe periscope circular display shall provide the following: 

a. Outer view of the horizon circle. 

b. Center downward view of the spherical earth. 

c. High and low magnification of the center view of the 
point where the vertical intersects the earth's sxirface. 
Ihe low magnification shall provide u complete horizon 
to horizon view. The high magnification center field 
view shall- provide a maximum of 30 degrees with magnifica- 
tion increased accordingly. 

d. Target index located in the center for definition of 
earth position relative to intersection of vertical with 
the earth's surface. ' 

e. Adjustable altitude indices and visual altitude indication. 

f • Attitude indices for indication of pitch and roll attitudes. 

g. -U3 degree retrograde pitch attitiade fixed indices. 

h. Fixed reticle lines for alignment of the capsxile normal 
axis with the earth vertical. 

i. A -lU^ 30 ' true vertical index on upper portion of display. 

j. Drift indices and drift set scale for capsule orientation 
with the groiand track. 

k. Sun-mocm index - A graduated settable 36O degree index about 
the perimeter for measurement of the angle of the rising or 
setting Sim or moon relative to the capsule longitudinal axis. 



MAC 23 1 CM (IOMAIV9SI 



HATP 20 January I96I 

REVISED 

REVISED 



M? 




^otdiion fAGE 



k2 



ST. Loms, Missoun 



REPORT 



ggp-^.u 



?»»vi -1 i II i)<^:ji M * « i«^ 



Monw Mercury Ca-psnl^ 



3.16,1 



PEEIISCOPE - (CoQtinued) 



The lower optical portion of the periscope and the periscope 
access door shall extend or retract automatically with provisions for Tnamiai 
override. Automatic extension and retraction shall occur in less than 8 
seconds eaclx. An amber light located on the upper left of the periscope 
display shall illuminate at any time when the lower optical portion of the 
periscope is in any position between located extended and locked retracted 
in the retract cycle. 



MAC 231 CM (lOMARSai 




„,„ 30 ^uary I?6l MCDONNELL ^ ^^^^^^ ,,,. U3 

REVISED ST. LOUIS, MlSSOIttl REPORT 6602^3^ 

REVISED ^3|i^H>^*1W3^ MnnP. Mercury Capsule 



3.17 lAiroiNG AMD POST-LANDING SYSTEI4S - A capsule landing system 

shall be provided, consisting of components tabulated in 
Appendix I-C herein. Item 10 « The landing systoa in accordance with MAC 
Drawing No. ii-5 -41700 shall include two independent parachute systems, 
sequencing controls, and post-landing equipment. All parachutes, harnesses 
and parachute bags as specified herein shall be inspected and paclsed at 
Port Canaveral, where they will be shipped directly to the launch site. 

3.17.1 LANDING SYSTEM - Uae landing system shall consist of a primary 

system comprising a main parachute, a drogue parachute, and 
associated sequencing controls. !Qie reserve parachute system shall be 
installed but shall be inoperative on this capsule. Obe landing system 
sequencing controls shall be anned by the tower separation sensor. For 
missions aborted between 10,000 feet and kO,Q00 feet, a time delay between 
escape tower jettison and drogue chute deployment of a minimum of two (2) 
seconds shall provide a sufficient time lapse required for various functional 
sequence during the abort maneuver. For missions aborted at an altitude 
below 10,000 feet, a second time delay of two (2) seconds shall prevent 
simultaneous actuation of the drogue mortar and the antenna fairing ejector. 

3.17.1.1 DROGUE PABACHUTB SYSTEM - A six (6) foot diameter conical 

ribbon type drogue parachute assembly with a thirty (30) foot 
bridle length, shall be provided for adequate dynamic stability and decelera- 
tion during the re-entry phase. The drogue chute shall be constructed of 
cotton, nylon and dacron materials and shall be designed for a dynamic 
presstnre of II6 poxonds per square foot considering deployment at a geometric 
pressure altitude of Uo,000 feet. The drogue chute shall be stowed in a 
drogue chute bag. This assembly and a mortar sabot shall be located in the 
drogue mortar tube. At k2,0OQ feet barometric pressure altitude, a barostat 
(aneroid pressure switch) shall receive static pressure from the recovery 
compartment, close a switch and complete an electrical circuit to a 
cartridge squib located under the mortar tube, initiating a gas charge. 
!Qie gas charge shall force the mortar sabot, and drogue chute assembly 
from the mortar tube causing the chute to deploy. Obe drogue chute shall be 
attached to the antenna fairing by a 3-riser arrangement and shall be 
released by jettison of the antenna fairing. 

3. 17. 1*2 MAIN PARACHUTE SYSTEM - 'Ihe main "parachute assembly shall be a 

sixty- three (63) foot diameter reefed (12 percent for k seconds) 
ring-sail type parachute designed to provide a stabilized sinking speed of 
thirty (30) feet per second at five thousand (50OO) feet altitude for a two 
thousand one hundred sixty (2l60) pound capsule. The main parachute of nylon 
material shall be designed and constructed to withstand shocii loads encoun- 
tered at ten thousand (10,000) feet deployment altitude at velocities up 
to 295 feet per second true velocity. It shall be considered that there has 
been no velocity decrement occasioned by drogue chute deployment, so that 
drogue chute failure cases shall be completely covered. Die msiin parachute 



MAC Z3t CM (10 MAI^ S6» 



,.„.o^^.,., M^DONNELL^ ^^^^ 



"Evisa ST. LOWS, Missoun 

REVISED 



-^v'Hd a *'«!*#* 



PAriF 


kk 


»PPn»T 


66o^.iU 


Mnnw Mercury Capsule 



3.17-1.2 MAIN PARACHUTE SYSTEM - (Continued) 

sJaall be stowed in the cylindrical recovery compariiaent aft of the conical 
afterbody and its deployment bag lanyard shall be connected to the antenna 
fairing so that upon antenna jettison, the main chute, as it pulls out of 
the chute pack, shall be deployed. A parachute deployment bridle, fabricated 
f3rom 750# tubular nylon webbing, shall be attached to the apex of the para- 
chute in such a manner that the loads encountered upon parachute deployment 
shall be distributed syimnetrically about the apex. This shall take place 
at ten thousand (10,000) feet geometric pressure altitxide as sensed by a 
barostat (aneroid pressure switch). The barostat shall complete an electrical 
firing circuit to the antenna fairing ejector asseably subsequently jettison- 
ing the antenna fairing. The barostat shall also initiate extension of the 
periscope. Upon sepeuration of the antenna fairing, the main chute ejector 
gas generator asseably shall be electrically initiated, and shall produce 
gas for injection into the main parachute ejector bag, which, with the 
antenna fairing, shall eject the main chute pack from the recovery compart- 
ment. As this occurs, the main chute shall pull out of the main chute 
deployment bag, releasing the antenna fairing, drogue chute and bag. At 
the time of main chute ejection, a SOFAR (dummy) bomb shall be ejected, 
(see Paragraph 3.17.2.1). Separation of the antenna fairing shall . energize 
the cabin air inlet and exhaust valve "open" circuit for ventilation in 
low altitude abort maneuvers; switch from the bicone antenna to the UHF 
descent antenna; and, after a twelve (12) second time delay shall ajm the 
impact sensor (dual inertia switch), and the pressure switch. Gore colors 
of the main parachute shall be natiaral and international orange alternately 
arranged. 

3.17.1.3 PILOT PARACHUTfa! - The pilot parachute shall be installed on 
this capsiile but shall be incapable of being deployed. 

3 •17.1.^ RESERVE PARACHUTli - The reserve parachute assembly shall be 
insta3J.ed on this capsule but sha3,l- not be capable of beizig 
deployed. At the time of reserve chute ejection, fluorescein dye marker 
package, attached to the capsule by a lanyard, shall be ejected. (See 
Paragraph 3«17«2*2). In a noimal landing sequence, the reserve chute shall 
be ejected from the capsule through the closed "rescue aids" toggle switch 
(P-15) after the pressure sxd.tch or the impact sensor (dual inertia switch) 
has become aaergized. The reserve chute shall also be ejected after run-out 
of a ten (10) minute time delay which shall become energized by closure of 
the impact sensor (dual inertia switch) upon impact. This time delay shall 
bypass the "rescue aids" toggle switch, and shall energize the same cir- 
cxiitry as the closed "rescue aids" toggle switch (P-I5). 



MAC 231 CM CIOMARSSI 



REVISED ^- — ST, LOUIS M|;^fjp'rrT , , pir ^^^^ 6603-14 

REVISED jB^^^^^TTA^* AAnnPi Mercury Capsule 



3*1T^2 POST-LAHDING SYSTEM - The post-landing system shall include 
one SOFAR (durnmy) bomb, fluorescein dye marker package, and 
inertia switches for actuation of eqiiipment essential to recovery. 

3.1T-2.1 SOFAR BCMB - One (l) dummy SOFAR banb shall be installed and 

shall be ejected at main chute deployment at 10,000 feet 
altitude. 

3.17.2-2 FLUORESCEIN D'YE MAEKER - A fluorescein dye marker package shall 

be provided to aid in visual location diiring the search phase. 
In a noxmal landing sequence, the marker package shall be ejected after 
reserve chute ejection and Impact on the water. !I3ie powder shall be ^ 
packaged in a water soluble container enclosed by a perforated metal ^can 
attached to the capsule by a retainer line. 

3-17-2.3 RECOVERY FLASSPiG LICST - A high intensity flashing recovery 
ligtit in accordance with MAC Drawing No. ^5^6702 shall be " 
provided. Flashing rate of the light shall be at least fifteen (15) 
flashes per minute at an intensity which shall be visible below twelve 
thoixsand (12,000) feet at a distance of approximately filly (50) nautical 
miles on a starlit moonless nl^t. at, a relative humidity of at least ninety 
(90) per cent, ate ligjat shall iave self-contained batteries. 

3.17-2.i<- IMPACT SENSOR - Hie impact sensor (dual inertia switch) shall 
initiate the following functions: 

a. Initiate main parachute disconnect. 

b. Initiate the reserve parachute ejector and disconnect and 
the pilot parachute deployment gun through the closed 
"rescue aids" toggle switch (P-I5). 

c. Energize a ten (10) minute time delay which shall, upon 
run-out, initiate the reserve parachute ejector and dis- 
connect axid the pilot parachute deplo^^ment gun in the 
event that the "rescue aids" toggle switch (P-15) shoxild 
not be closed* 

d. Start recovery flashing ll^t. 

e. De-energize excess communications and'. instrumentation. 

f • Energize a time delay to maintain low and high frequency 
telemetry units and the tape recorder until ten (10) 
minutes after impact. 



MAC 231 CM (to I 



REVISED Sr> lOUIS> MiSSO UM ^^^^ ^^93^ 

REVISED jJIILn^ii^CTBftWl f y^fciatr MOOa Mercury Capsule 



3.18 HAHDUMG EROVISIQETS - A hoisting loop assembly in accordance 
with MAC Drawing No. ^5-32263 shall be provided for capsule 

pick-up by helicopter. The loop shall be attached to the recovery compart- 
ment structuiul assembly by two hoist loop support fittings. Dae hoist 
loop shall constructed of 9,000 pound capacity dacron webbing with a fiber- 
glass plastic spring strap taped to the dacron to cause the loop to erect 
upon ejection of the antenna fairing. Two auxiliary hoisting fittings in 
accordance with MAC Drawing Ho. ^4-5-32068, located at capsule station line 
2023.00 shall be provided. 

3.19 SUPPORT EQUIPMEST - Stfl3port equipment for Merctary capsiole 
shall be as separately negotiated in CCF 52 Series. 

3.20 FZROTECHHICS - Pyrotechnic devices in accordance with MAC 
Drawing No. 45-72OOI (as specified in Appendix I-C, Item 11 

herein) shall be provided for the following: 

a* Unbilical disconnect 

b. Capsule-adapter clamp ring separation 

c. Tower clamp ring separation 

d. Retrograde package release 

e. Parachute deplo^ent and disconnect 

f . Antenna fairizig ejection 

g. Snorkel valve actuation 

h. Snorkel inlet door 

Pyrotechnics with the exception of snorkel valve squibs shall be installed 
at the laxmch site. 



MAC 231 CM (10MAMM» 



..„ 30 ,.n^ m MCDONNELL ^ ^^^^^^^ ,^ y_ 

REVISED ST. LOUIS, MISSOWU REPORT 6^Q3=2k 

REVISH) .•#.^y[iLP:ff ilJH' W'l' fcA-ty AAnnw Mercury Capsule 



i^.O QUftLUTCATiaiT 

^.1 MAC QUALIFICATION - Qualification of eq.uipnient and svib systems 

shall be accomplished by WkC or by stibcontractors under MAC 
direction as defined in MAC Report 6^95 and in component specification con- 
trol drawings* Qualification statxis of parts shall be as tahialated in MAC 
Drawing No. 45-OOOO3. 

k.2 NASA QUALIFICATION - Ohe capsules supplied by the contractor 

will be used in a qualification flight test program to be con- 
ducted by the NASA. The capsule and its systems shall demonstrate satis- 
factory performance within the framework of this specification. This quali- 
fication program 'will have as its final objective the acccraplishm^it of the 
missions described in Paragraph 1,1.1 herein* 

5.1 MAC TESTING - Die contractor shall landertake structural, aero- 
dynamic, hydrodynamic, e<iuipment, compatibility, acceptance, 
and evaluation tests as required In support of the capsule development pro- 
gram. 

5 '2 NASA TESTING - A program of research and development fligjit 
testing of the capsule will be undertaken by the NASA. This 
program will include full-scale flight tests of simplified capsules of which 
Capsule No. Ik shall be a part. 

6.0 DKfc'iNITION - 

NASA National Aeronautics and Space Administration 

MAC McDonnell Aircraft Coarporation 



MAC 231 CM flOMAMMI 



nATB 20 January 196l 

REVISED 

REVISED 



MDONNELL 



^tcte*^ Loybc 



notation page llL 

ST. LOUS, MISSOUM REPORT ^^3-1^ 



MODB.lfei; 



_C^S23lfi. 



APPEHDIX I-A 



GOVERMMEMT FUBNISHED EQUIiMEHT - COMTRACTOR INSTALLED 



ItesL 


Qty. 


Nomenclature 


1 


1 


Adapter Extension Assy. 


1.1 


1 


Capsule Matcb Ring 


1.2 


1 


Top Adapter Blng 


1.3 


1 


Bottom Adapter Ring 


l.lf 


1 


Pressure Plate 


2 


1 


Periscope (See Para. 3.I6.I) 



wt. 



Identification 
NASA: 803305 
NASA: LC 803297 
NASA: LC 803295 
NASA: LC 803296 
NASA: LE 80286I 
MAC: 1^5-86T01-3 



MAC 231 CM (to MAR SOl 



HATP 20 January 1961 

REVISED 

REVISED 



MDONNELL 



',^>^«4tft<ar L^oybotd&m 



PAGE 



'^9 



ST. LOUIS, MISSOUM 



REPORT 



66Q^-lij- 



Mnnn Merciir'/- Capsule 



APPENDIX I-B 



GOVEEaiMECn? FORTJISHED SQUIPMEHT - GC3VEEHMENT IHSTALLED 



Item 

1 

2 



1 
1 



Momenclature 

Basic Adapter 

Special Atlas Adapter 
Pdng (Para. 3.7) 



Wt. 



Identification 



MAC 1*5-33501-3 



MAC 231 CM (10 • 



HATP 20 January 1Q61 



M?DONNEU 



37^*^«i^7^ L^rt^otdtunt 



PAGE 



JO 



REVISB) 



ST. LOUIS, MISSOUM 



REPORT 



6603-l^ 



RFVISFD 










APPENDIX I-C 








COHTRACTOR-FUENISHED EQUIUffiHT - CONTRACTOR lMK'l'AT.T.m 






GENERAL 










IDENTIFICATIOII 


Item 


Qty. 


Nomenclature 


MAC No. 


Mfg. No. 


1 




Genexal Assembly, Mercuiy 
Indudlng: 


1*5-00001-59 


_ . _ 


1.1 


1 


Structural Assembly, lyion 


1*5-31001-315 


_ _ _ 


1.2 


1 


Antenna Assemblyj CToimmml- 
cations 


1*5-31003-305 


- _ _ 


1.3 


1 


Capsule Assembly 


1*5-32000-319 





1.3.1 


1 


Structural Assembly, 
Capsule 


1*5-32001-303 





1.3.1.1 


1 


Structural Assembly 
Conical Section 


1*5-32002-303 





1.3.1.1.1 


1 


Window Assembly, Capsule 
Inner (Forward Viewing) 


1^5-35035-301 


_ - _ 


1.3.1.2 


1 


Structural Assembly 
Cylindrical Section 


1*5-32003-301 


- - - 


1.3.2 


1 


Shingle Installation, 
Capsule 


1*5-3221*5-303 


- - _ 


1.3.3 


1 


Insulation Installation 


1*5-32038-309 


- - - 


1.3.^ 


1 


Heat Sink Assembly 


1^5-32051-305 





1.3.5 


1 


Door Assembly, Periscope 


1*5-32091-301 





1.3.6 


1 


Fin, Periscope Door Hinge 


1^5-32093-3 





1.3.7 


1 


Window Assembly, Capsule 
Outer 


1^5-35030-l 


_ _ - 


1.J+ 


1 


Provision Instal. -Little 
Joe Adapter Wiring 


1^5-33550-1 





MACUtCM (tOMARSM 



nATg 20 Jaauajy 196l 

REVISED 

REVISB) 



MCDONNELL 



^^y^ute^fm- L^oybotd&m 



PAGE 



51 



ST. LOUS, Missoun 



iiii3*viUii'il?» 



RBORT. 



66ovil» 



urtm Meretiiy Capsule 







AFFEHDEC I-C 




'• 




COMTBACTQR-PORHISHED BQUIEMEHT - CONTRACTOR raSTALLED 






(iiillEHAL (Continued) 








HJEHTIFICATIQII 


Item 


QtjT. 


Nomennlaturft 


mc No* 


Mfg. No. 


1.5 


1 


System Installation^ 
Recoveiy (See Item 10) 


1^5-lH001-3lJ'*- 


^ • . 


1.6 


1 


Rocket Instaiajatlon 
Retrograde (See Item 2) 


iv5-5OOO1.307 





1.6.1 


6 


Spacer, Adjusting Retro 


if5-500li^-5 


.. - - 


1.6.2 


3 


Retention Assenfbly, Retit)-* 


^5-72030-301 


- - - 


1.7 


1 


(See Item 2) 


1^5-51001-311 





1.7.1 


1 


Escape Rocket Structural 
Assembly 


lf5-510Q2-305 





1.7.1.1 


1 


Ballast, Hose 


lf5-51010-301 





1.7.1.2 


2 


Fairing, Rocket Junction 
Box Lug 


1^5-51021^-1 


- - « 


1.7.1.3 


2 


Pairing, Escape Rocket 


U5-51023-I 





1.8 


1 


System Installation, 
Pyrotecbnlcs (See Item 11) 


1^5-72001-ll|. 


- - - 


1.8.1 


1 


Installation Conical Fair- 
ing Syion to Capsule 


1^5-720^5-1 





1.8.1.1 


1 


Fairing Assembly, I^lon 
to Capsule, Conical 


l^5-720U3-l 





1.8.2 


1 




1^5-72010-7 


- - - 


1.8.3 


1 


Installation, Antenna 
Fairing Ejector 


1^^5-72020-303 





dot 



DATE 

REVISB) 

REVISB) 



20 .TftinarT 1961 MiDONNELL ,^^ ^ C^botdean, 



ST. LOWS, Missown 



PAAS 


52 


REPORT 


66o^-iU 





Item 
1.8.1* 

1.9 

1.10 

1.11 

1.02 

1.13 
l.l»* 

1.15 

1.15.1 
1.15.2 
1.15.3 
1«16 

1.16.1 



APli'ENDIX I-C 
CQHTRACTOR-FUftlllSHED EQUIBiEin.' - COHTRACTOR mSTAIIED 

GEHEBAL (Coixtlnaed) 

HEHTIFICATIOH 
Ncmenclature MAC Ho. Mfg. Ho. 



1 



1 
1 



1 

1 

1 
1 
1 
1 



Installation^ Retaining 
Bing, F^lon to Capsule 

Electrical Installation, 
Escape Rocket 

Electrical Installation, 
pylon 

Electrical Installation, 
Antenna Fftiring 

Electrical Installation, 
Midsection 

Electrical Installation, 
Retxoroclset 

Electrical Installation, 
Adapter Little Joe 

Eqniioent Installation 
(See Items 3A/5»6,7>8 & 9) 

B.H. Console Panel 

Ilain Instrunent Panel 

Panel Asseabl7, ^.B. Console 



MAC Ho. 
l*5-72(AO-l 

U5-770OO-I 

11.5-77001-301 

1*5-77002-303 

I1.5-78OO3-313 

i*5-78ooe 

1I-5-79100-1 

l*5-800ll|.-l 

1*5-83027-13 

1*5-81100-309 

1*5-81110-303 



Instrumentation Installation 1*5-88510-317 
Special, Consisting of: 



1 Crushable Support Assoably 1*5-82001-35-11* 



MACMI CM (lOMMMl 



nATP 20 Jannaiy I96I 
REVISB) 



M^OMELL 



37^»««p L^oybotd£o7i 



PAGE 



53 



ST. tous, Missoun 



REPORT 



66cn--Lh 



BEVISH) , „ 




— £tAitfHif IMWHl liif iunnn Jfercury Capstile 






APEEHDIX I-C 








COimiACTOR-lf'UHBIiaHED JdQUIPMEHT - COMTRACTOR HJSTALLE 


D 
CATiaU 




GEHEEtAL (Cozrtlzxued! 






Item 


Qty. 


Ncanenclatxire 


MAC Ho. 


Mfg. No. 


1.16.2 


1 


Crashable Si^port Assesaibly 


i^5-a20Ql-39-l^ 


1.16.3 


1 


Crushable Support Assembly 


k3-azooi-h3-lk 


1.16.1|. 


1 


Crushable Stcpport Assembly 


1^5-82001-47-11^ 


1.16.5 


1 


Crushable SuEport Assembly 


U5-8200I-5I-14 


1.16.6 


1 


Shelf AssesBLbly-^Accelercoeter 
and Rate Gyro, Includljig: 


k3^88^3-l 





1.16.6.1 


* 


Relay P^uiel Assembly 


1^5-78016-1 


- - ■- 


1.16.6.2 


« 


Inverter 


1^5-79709-3 


Interelectronics 
28!ri5A40GB-2 


1.16.6.3 


* 


Filter 


1^5-79709-7 


Interelectronics 
2aFA30GHA-2 


1.16.6.4. 


# 


Cover 


1^5-79727-17 


Harris: 
33000.17 


1.16.6.5 


-» 


Cover 


1^5-79727-19 


Harris: 
33000-19 


1.16.6.6 


♦ 


Fuse Block 


1^5-79727-^7 


Hsirrls: 
33000-U7 


1.16.6.7 


1 


Accelesroaneter and Rate 
Gyro Pftclsage 


lfr5-88870-7 





1.16.7 


1 


Shelf Asse9aA>ly<-Accelerameter 
and Rate Gyro, Including: 


1^5-885^5-3 





1.16.7.1 


1 


Pallet Assembly 


1^5-88501-309 





* See Electrical Section, Item k herein. 


for Quantities 


. 



KMCaSI CM (10 MAR Ml 



OATP 20 January I96I 

REVfSEa - 

REVISH) 



MCDONNELL 



Item 
2 

2.1 

2.2 

2.3 

2.U. 



nuie*^ Lc^ftd&m 



PAGE 



5^ 



ST. LOUS, MISSOUM 



REPORT 



66q?.iU 



H -1. \ #^: 



Mnnn Mereurv OapanlP 



APPENDIX I-C 



3 
3 

1 



COMERACTOR-FUENISHED EQUHMEHT ■ 


- CONTRACTOR INSTALLED 


ROCEET mSIALLAIIOBS 






IDEMTIPICATION 


r. Nomenclature 


MAC No. 


Mfg. No. 


Caps\ile Bocket Instal- 
lations 






Rocket Assembly, Dummy 
Retrograde 


1*5-50700-9 


Thiokol 


Rocket, Dummy Poslgrade 


1*5-50701-9 


Atlantic 
Research: 


Rocket, Escape System 


1*5-51700-3 


Grand-Central 
1*77-80100 


Rocket, Pylon Jettison 
Tri -Nozzle 


1*5-51701-15 


Atlantic- 
Research: 
E-20189 



MAC 231 CM (lOMAHSS) 



nATP 20 January 1961 
REVISED 



M?DONNEll A 



^cie^m' Lc^6 



55 



^Otd&On PAGE 

ST. LOWS, MISSOUM REPORT ^^Q3=i]* 





RFvisro 




'^'^''"^MrfMft^Hiib 


1^^^ AAOOa 


Mercury Capsule 








APPENDIX I-C 










CONTRACTOR-FURNISHED EQUIPMENT - 


CONTRACTOR INSTALLE 


D 






AIRBORNE EQUIPMENT 










IDENTIFICATION 




Item 


Qty. 


Nomenclature 


MAC No. 


Mfg. No. 




3 




Alrl)ome Eqialpment, 
Consisting of: 








3.1 


1 


Satellite Clock (Interim) 


i*5-8l059-305 






3.2 


1 


D.C. Voltmeter 


45-81716-3 


Weston 

Instrument: 

183537 




3.3 


1 


D.C. Ammeter 


U5-8I7I7-3 


Weston 

Instrument: 

183538 




IX 


1 


A.C. Voltmeter 


45-81718-3 


Weston 

Instrxment: 

183539 




3.5 


1 


Transducer (Pitch) 


45-81721-13 


Minneapolis- 
Honeywell: 
GG 134A-4 




3.6 


1 


Transducer (Boll) 


45-81721-15 


Mlnneapolis- 
Honeyvell: 
GG 134A-5 




3.7 


1 


Transducer (Yaw) 


45-81721-17 


Mnneapolis- 
Honeyvrell: 
GG 134A-6 



MAC 231 CM (10 MAII 9«> 



REVrSEir: ST. LOWS, MlSSOmi REPORT $^Q^-l4 

REVISED mSSSS^MMB^^SMIBUBM Mnna Mereirrv Capail.A 



APPEMDIX I-C 
COMTRACTCR-FURIIISHED EQUIFMEICT-COHTRACTOR INSTALLED 

ELECTRICAL 

IDEHTIPICATION 



Itaa 


Qtjr. 


Nomenclature 




MAC No. 


k 




Electrical Equipment 
Consisting of: 




- - - 


Iv.l 


1 


Diode Panel Assembly, 
Power System Control 




45-78012-317 


k.2 


1 


Relay Panel Assembly, 
Claatp Ring Separation 




45-78041-301 


k.3 


1 


Relay Panel Assembly, 
Power System Control 




45-78081-339 


h.k 


1 


Relay Panel Assembly, 
Power Systen Control 




45-78081-337 


^'3 


1 


Relay Panel Assembly, Launch, 
Orbit and Escape Sequential 


45-78084-307 


k.6 


1 


Relay Panel Assembly, Launch, 
Orbit and Escape Sequential 


45:-78084-353 


h.7 


1 


Relay Panel Assanbly, Launch, 
Orbit and Escape Seq:iiential 


45-78084-327 


k.a 


1 


Relay Panel Assembly, 
Retrograde Sequential 




45-78085-357 


h.9 


1 


Relay Panel Assembly, 
Recovery Sequential 




45-78086-369 


4.10 


1 


Relay Panel Assembly, 
Recovery Sequential 




45-78086-381 


4.11 


1 


Relay Panel Assembly 
Communication and Periscope 


45-78089-313 


4.12 


1 


Relay Panel Assembly, 
ASCS System 




45-78090-341 



Mfg. Ho. 



MAC 231 CM {lOMAfl9«> 



nATP 20 January 196l 
REVISED 



MTOMELL 



3^'^4<?faafr LyoybotdGan 



PAGE 



57 



ST. LOUIS, MISSOUU 



REPORT 



66ot-i1» 



pfvisi;n 




— SggBBBBBBSSBit 


901 AAnnn Mercury Cansule 






APPKNDIX I-C 








COHTRACTOR-FIJENISHED EQUIPMENT-CONTRACTOR INSTAT.Tm 






Er.H:PRICAL (Continued) 




-- 




IDEKTIPICAIION 


Item 


Qty. 


Nomenclature 


MAC Nb. 


Mfg. No. 


1^.13 


1 


• 

Belay Panel Assembly, 
ASCS System 


U5-78O9O-333 


- - - 


l*.ll* 


1 


Relay Panel Assembly, Instru- 


45-78092-309-11^ - - - 






mentation Control System 






1^.15 


6 


Battery (1500 Watt-Hour) 


45-79707-19 


Eagle Pitcher 
MAR-4028-B 


lv.l6 


1 


Static Inverter (250 VA) 


45-79709-1 


Inter electronics: 
28a?15A4QHA-2 


1*.17 


2 


Static Inverter (150 VA) 


"^ 45-79709-3 


Interelectronics: 
28a715A40GB 


lv.18 


3 


Filter Assembly 


45-79709-7 


Interelectronics: 
28FA30aEA-2 


lv.l9 


56 


Power and Control Relay 


45-79712-2 


PUtors: 
P26A1H6A9 


2^.20 


39 


Power and Control Relay 


45-79712-8 


Pott er-Brunf 1 eld : 
SL4080-1 


U.2L 


If 


Power and Control Relay 


45-79712-12 


Leadi: 
9227-5369 


^.22 


3 


Power and Control Relay 


45-79712-15 


Leach: 

9226-5368 


1<..23 


7 




45-79712-16 


Leach: 
9224-5367 


U.2U 


\ 


Power and Control Relay 


45-79712-33 


Piltorsi 
26SHI8P 


If. 25 


11 


Power and Control Relay 


45-79712-34 


Plltors: 
L126E3.8 


U.26 


14 


Power and Control Relay 


45-79712-19 


Leach: 
9229-5371 



MACm CM (lOMARMl 



nATP 20 January 
REVISED 



m MDQNNM^^ 



ST. LOUIS, MISSOIMI 



notation page L 

REPORT ^^3-lt^ 



REVISED 




_ ^HB^iSfinWvi 


m MOOB. Mercury Capsule 






APPENDIX I-C 








COHTRACTOR-PIIMIISHED EQUIPMEHT - COHTRACTOR INSTAT.T.K 


D 




ELECTRICAL (Continued) 










IDEMTIPICATIOir 


Item 


Qty. 


Nomenclature 


MAC No. 


1 
Mfg. No. 


U.27 


lU 


Power and Control Relay 


1^5-79712-21 


Leach: 
9220-5366 


U.28 


3 


Power and Control Relay 


1^5-79712-22 


Leach: 
9228-5370 


U.29 


3 


Power and Control Relay 


1^5-79712-23 


Leach: 
9223-5375 


U.30 


1 


Power and Control Relay 


1^5-79712-26 


Leach: 
9271^-5300 


lv.31 


2 


Power euad Control Relay 


lf5-797l2-27 


Leach: 
9271^-5377 


I1..32 


2 


Power and Control Relay 


l*5-7971?-28 


Leach: 
9229-5372 


1*.33 


2 


Power and Control Relay 


45-79712-32 


Leach: 
9220-5378 


1^.3^ 


\ 


Limit Switch 


1^5-79713-39 


Hfeydon Switch 
61I122 


4.35 




Removed 






U.36 


7 


Push Button 


1^5-79713-23 


Eaydon Switch 
61375 


»*.37 


6 


Guard 


1*5-79713-25 


Electro-Snap 
U2-OU1 


1^.38 


12 


Idmtt Switch 


1*5-79713-29 


Electro-Snap 
KX5-1*-1 


1^.39 




Removed 







MAC 231 CM <tOMAN9«> 



REVISB> 



MfDOMELL 



•^ioieua^ Loybi 



'otd&m, PAGE 



59 



ST. uHns, Missoini 



REPORT 



6601-14 



BirVISH) 










APPliM)IX I-C 








COHTRACTQR-FURNISHED EQtJIPMEMT - 


COOTRACTOR INSTALLED 




ELECTRICAL (Continued) 










IDEOTIFICATION 


Item 


Qty. 


Ifomenclatxure 


MAC No. 


Mfg. No. 


U.UO 


2 


Limit Switch 


^5-79713-71 


Electro -Snap: 
H11-12T 


hXL 


1 


Limit Switch 


1*5-79713-63 


KLectro-Snap: 
mi -122 


1^.42 


2 


Limit Switch 


1*5-79713-67 


Electro-Snap: 
HIT -124 


J*A3 


1 


Limit Switch 


1*5-79713-57 


Electro-Snap: 
Hll-119 


U.IA 


1 


Limit Switch 


1*5-79713-73 


Electro-Snap: 
Fl,l-128 


hM 


4 


Limit Switch 


1*5-79713-65 


Electro-Snap: 
Hll-123 


\.)*& 


2 


Limit Switch 


1*5-79713-69 


ELectro-Snap: 
•El.l -125 


\.\1 


3 


Limit Switch 


1*5-79713-59 


KLectro-Snap: 
Hll-120 


U.W 


5 • 


Relay - Time Delay 
2 Seconds 


1*5-79715-1 


Wheaton: 
E371-A 


l^.lt9 


3 


Relay - Time Delay 
5 Seconds 


1*5-79715-7 


Wheaton: 
E371-D 


lv.50 


2 


Relay - Time Delay 
10 Seconds 


1*5-79715-11 


Wheaton: 
E371-E 


lv.51 


3 


Relay - Time Delay 
20 Seconds 


1*5-79715-15 


Wheaton: 
E371-G 


U.52 


2 


Relay - Time Delay 
30 Seconds 


1*5-79715-17 


Wheaton: 
E371-H 


If. 53 


1 


Relay - Time Delay 
300 Seconds 


1*5-79715-67 


Wheaton: 
E376-A 


It. 54 


2 


Relay - Time Delay 
30 Seconds 


1*5-79715-37 


Wheaton 
E372-E 



MAC 231 CM (10««AIIS«» 



REVISS 




— ST. LOUIS. Missoun 


yybotaHon. page ^. 

REPORT ._. (^fi^'W 


BEVISEn 




- ItfniilUIEPTXUJ^ "nn« Mercury Capsule 






tS?ESDTL I-C 








COOTSACTOR-PURNIBHJja) EftUIPMEWP - CCJKTRACTOE TTlRTATJJBf 


D 




ELBOEBICia. (Contimied) 










nJBBTIPICAPION 


Item 


Qty. 


Nomenclature 


MAC No. 


Mfg. Ho. 


1^.55 


3 


Relay - Time Delay 
60 Seconds 


^5-79715-39 


Wheaton: 
5372-P 


k,36 


1 


Belay - Time Delay 
150 Seconds 


1^5-79715-^3 


Uheaton: 
E375-D 


i^.57 


2 


Relay - Time Delay 
600 Seconds 


1^5-79715-1^5 


Uheaton: 
BI109 


^^.58 


2 


Relay - Time Delay 
3 Seconds 


1*5-79715-51 


Wheaton: 
B372-G 


l^.59 


2 


Relay - Time Delay 
10 Seconds 


1*5-79715-53 


Wheaton: 
JJ3Y2H 


k.6o 


3 


Relay - Time Delay 
1 Second 


1*5-79715-55 


Wheaton: 
E372J 


^^.6l 


U 


Relay - Time Delay 
12 Seconds 


1*5-79715-57 


Wheaton: 
E372K 


1^.62 


2 


Relay - Time Delay 


1*5-79715-61 


Wheaton: 
EI7I* 


1^.63 


2 


Relay - Time Delay 
2 Seconds 


1*5-79715-63 


Wheaton: 
JS372R 


»f.61f 


1 


Telellght Assembly 
Consisting of: 


l^5-79720-llH 


Grimes: 
333l»0-llH-327 


lf.61v.l 


1 


Clip 


1*5-79720-45 


Grimes: 
333l«3-l*5 


J^.61v.2 


2 


Light Assembly (Red) 


lfr5-79720-li7 


Grimes: 
3331*0-1*7-327 


k,6k,3 


1 


Light Assembly (Green) 


1*5-79720-49 


Grimes: 
333lK)-49-327 


h.6k.k 


1 


Nomenclature Cap (Tower 
Jett.) 


1^5-79720-11^3 


Grimes: 
333l«)-ll*3 



MACaat CM (tOMARSM 



nATP 20 .Tnimftry iqgl 

REVISB) 

REVISB) 



MCDONNELL >^ 



^T-^^^fca^ C^- 



^otatiort PAGE 



a 



ST. LOWS, Missoun 



REPORT 



3^S2c^ 



AAnna Mercury Capsule 







Ai'i'iiiNUU I-C 








COHTRACTOR-PORIIISHED EQUIiMEHT - CDHTRACTOR IKSTALIEl 


D 




ELECTRiaAL (Continued) 












Item 


Qty. 


Nomenclature 


MAC No. 


Mfg. No. 


lv.65 


1 


Telellght Assembly 
Consisting of: 


'^5-79720-ll^5 


Grimes: 
333^-145-327 


lf.65.1 


1 


Clip 


1^5-79720-45 


Grimes: 
333lK)-45 


lfr.65.2 


2 


Light Assembly (Red) 


1^5-79720-24.7 


Grimes : 
3331(0-1*7-327 


V.65.3 


1 


Light Assembly (Green) 


lf5-79Tao-49 


Grimes: 
333l»0-49-327 


l^.65.1^ 


1 


Nomenclature Cap 
(Capsule Sep.) 


lf5-79720-ll«.7 


Grimes: 
333IW-147 


l^.66 


1 


Telelight Assembly 
Consisting of: 


^5-79720-11^9 


Grimes : 
333iW-l'*9-327 


l*.66.1 


1 


Clip 


lf5-7g720-l*5 


Grimes: 
333l»0-45 


^.6612 


2 


Light Assembly (Bed) 


l<-5-79720^7 


Grimes: 
333^-47-327 


l^.66.3 


1 


Light Assembly (Green) 


lv5-79720-i*9 


Grimes: 
333^*0-49-327 


Kee>,\ 


•1 


Nomenclature Cap 
(Retro Seq. ) 


1*5-79720-151 


Grimes: 
333i«)-151 


1^.67 


1 ■ 


Telelight Aaseobly 
Consisting of: 


1*5-79720-153 


Grimes: 
333i«0-153-327 


if. 67.1 


1 


Clip 


45-79T«JO-li-5 


Grimes: 
33340-45 


lf.67.2 


2 


Light Assembly (Red) 


1*5-79720-47 


Grimes: 
333i»0-47-327 


if. 67. 3 


1 


Light Assonbly (Green) 


1*5-79720-1*9 


Grimes: 
333liO-ii9-327 



MACm CM (tOMARSSl 



DAB »Jm»rTl9& MfflMlX^ /^^,^^ „„ te 


REVISB) 
REVISED 




— ST. LOWS, MISSOUM l»0"T 6603-U 

- *COf*F»fi{!HHUJL^ «nnB Mercury CaT,sul« 






i^FFENDIZ X-C 








CONTRADrOR-FnEaSISHED BQJUBEIST - CaUTRACTOR IHSTALT.KP 




EESCTBICAL (Contlmed^ 


1 










IDEHTIFICAnOK 


Itaa 


1 




MAC No. 
1*5-79720-155 


Mfg. No. 

Grimes: 
333^-155 


Nomenclature Cap 
(Betto Abt.) 


1^.68 


1 


Tftlellght Assembly*- 
Consisting of: 


1*5-79720-157 


Grimes: 
3331*0-157-327 


'1^.68.1 


1 


Clip 


1*5-79720-1*5 


Grimes: 
3331*0-45 


i^.68.2 


2 


Light Assembly (B^) 


1*5-79720-1*7 


Grimes: 
333lK)-1^7-327 


1^.68.3 


1 


Ligbt Assembly (Green) 


1*5-79720-1*9 


Grimes: 


l^.68A 


1 


nomenclature Cap 
(Fire Retro) 


1*5-79720-159 


Grimes: 
3331*0-159 


1^.69 


1 


TelftHght Assenbly 
Consisting of: 


1*5-79720-161 


Grimes: 
3331*0-161.327 


1^.69.1 


1 


Clip 


1*5-79720-1*5 


Grl&ies: 
3331*0^^5 


k.69.2 


2 


Light Assembly (Red) 


1*5-79720-1*7 


Grimes: 
3331*0-1^7-327 


U.69.3 


1 


Light Asseobly (Green) 


1*5-79720-1*9 


Grimes: 
3331*0-1*9-327 


U.69A 


1 


Nomenclature Cap 
(Jett Retro) 


1*5-79720-163 


Grimes: 
3331*0-163 


lv.70 


1 


Telelight Assembly 
Consisting of: 


1*5-79720-165 


Grinjes: 
3331*0-165-327 


1^.70.1 


1 


Clip 


l*5-79720J*5 


Grimes: 
3331*0-45 


I1..TO.2 


2 


Light Assembly (Red) 


1*5-79720-1*7 


Grimes: 
3331*0-47-327 


HUeai CM (lOMAIIMI 









nATg 20 Janaary 1961 



MDOMELL 



^^y'u te^^ L>oybotdtuj7i 



PAGE 



63 



ST. LOUIS, MlSSOUd 



REPORT 



6603 -lJ» 



RFVI.SFD 




tflWffigiLIIIIitilliBiilii^ AAnnn Mercury Capsule 






APEEHDIX I-C 








CKSSTRACTOR-FUBIIISHED EQUIPMENT - 


CQNTKACTCR ^K5TJiT.T.TTi 




ELECIBICAL (Contiz 


nied) 


EICN 


UMfSnfLCA 


Item 


Qty. 


Ncmenclature 


MAC Ho. 


Mfg. No. 


•^.70.3 


1 


iramenclatare Cap 
(Betract Scope) 


l>5-79720-l67 


Grljnes: 
333IW-I67 


1^.71 


1 


Teleli«ht' Assembly 
Conslstizig of: 


^5-79720-169 


Grimes: 
333l«)-l69-327 


lt..71.l 


1 


Clip 


U5-79720Jf5 


Grimes: 
333IW-45 


lf.71.2 


2 


T.lebt ABBoablj (Red) 


U5-79720-i».7 


Grimes: 
333l«3-47-327 


^^.71.3 


1 


Light Assembly (Green) 


lv5-79720-it9 


Grimes: 
3331*0-49-327 


^-.Tl.!* 


1 


Nomenclature Cap 
(0.05iB Switch) 


1«.5^79720-171 


Grimes: 
3331*0-171 


k.72 


1 


Tftlellghrt Assembly 
Consisting of: 


^5-79720-173 


Grimes : 
333l»0-173-327 


11-.72.1 


1 


Clip 


lf5-79720-45 


Grimes: 
333110-45 


lt.^72.2 


2 


Light itsseBibly (Bed) 


1*5-79720-47 


Grimes: 
333lK)-47-327 


lt.72.3 


1 




^5-79720-^*9 


Grimes: 
3331*0-49-327 


1|..72A 


1 


Nomenclature Cap 
(Main) 


U5-79720-175 


Grimes: 
3331*0-175 


I1..73 


2 


Telellght Assembly 
Consisting of: 


1*5-79720-177 


Grimes: 
3331*0-177-327 


l^•73.1 


1 


Clip 


1*5-79720-45 


Grimes: 
3331*0-45 


l^.73.2 


2 


Light JtssemblY (Bed). 


45-79720-47 


Grimes: 
3331*0-47-327 



MACaSf CM IIOMMISSI 



0^ ^,^^^ mmm^^^^^^ 

REVISED ST. 10IIIS, MBSOUH 



PAGE 



61^ 



«EPOKt 



SSOi-lk 



REVISED 










iSPFENDIX I-C 








CailTBACI0R-i<11KNliJUKD EQUHMEIIT - 


CONTIiACrOB INSTALLED 




ECSCEBICAL (Ccotis 


oied) 


noH 




Item 


Qty. 


UoBenclsfcure 


MAC No. 


Mfg. No. 


^.73.3 


1 


Light Assembly (Gre^ 


'*5-79720-l»9 


Grimes: 
333lK)Ji9-327 


^.73A 


1 


Scoenclature Cap (Rescue) 


l^5-79720-179 


Grimes: 
333IW-179 


1^.7l^ 


1 


Teleligbt Assembly 
Consisting of: 


'^5-797ao-l8l 


Grimes : 
333l*0-lfil-327 


lf.7lfr.l 


1 


Clip 


'*5-7972O-101 


Grimes: 
333l«O-101 


^.7^.2 


2 


Light Assembly (Amber) 


^5-79720-103 


Grimes: 
333lK)-103-327 


k.7k.3 


1 


Nomenclature Cap (Stand- 
by-DC Auto) 


45-79720-183 


Grimes: 
333lK)-lfl3 


h.75 


1 


Telells3it Assembly 
Consisting of: 


^^5-79720-lB5 


Girimes: 
333lK)-l85-327 


^.75.1 


1 


Clip 


^5-79720-101 


Grimes: 
333110-101 


»t.75.2 


2 


Light AssemUy (Amber) 


1^5-79720-103 


Grimes: 
333lK)-103-327 


l^.75.3 


1 


Nomenclature Cap 
(Standby - A.C. Auto) 


1*5-79720-187 


Grimes: 
333l»0-lB7 


lf.76 


1 


Light Assembly (Abort) 


1*5-79720-237 


Grimes; 
31*160-237-313 


h.TT 


1 


Teleljght Assembly 


lt5-79720-2ln 


Grimes: 
333I1O-2IH-327 


1^.77.1 


1 


Clip 


1*5-79720-1*5 


Grimes: 
3331*0-1*5 


II-.77.2 


2 


Light Assembly (Bed) 


1*5-79720-1*7 


Grimes; 
333I1O-I17-327 



MAeaai cm (iomaki 



^ 



nATP 20 January 196l 
REVISa) 



M?DONNm.^ 



^^y'ccic^tapf- Lxtybc 



^otdtian page — _^ 

ST. LOUIS, MlSSOUn RB^"T ^^^"^^ 



REVI.SED 




■^^^^^V' '^ ^ ^'^ ^4 ^ »j.w^4:4 ^ »; 4 


pi AAnnn Mercury Capsule 






APPJiNDJJt I-C 








CQSTBACTOR-Jf'UHNiaHJJID KQUliWKMT - CONTRACTOR INSTALLED 




KTiKCTRICAL (Contiimed) 












IDERTIFICiSEIOH 


Item 


qty. 


Nomenclature 


MAC No. 


Mfg. No. 


'^.77.3 


1 


Light ABsanbly (Green) 


1^5-79720-49 


Grimes: 
333l«-l«-327 


U.77»l»- 


1 


Nomenclature Cap 
(Landing Bag) 


1^5-79720-21^3 


Grimes: 
333l«-2l«.3 


1^.78 


2 


Plug, Tower Elec. Dis- 
connect 


1^5-79720-1 


Cannon: 
3988U 


l^.T9 


2 


Receptacle^ Tover Elec* 
Disconnect 


1^5-79722-3 


Cannon: 
39885 


U.80 


2 


Cover, Tower Elec* 
Disconnect 


1^5-79722-5 


Cannon: 
39886 


i*.8l 


1 


Receptacle/ Ibibillcal 
Disconnect Assembly 


1^5-79723-1 


Cannon; 
GMAQI7072-33 


1^.82 


50 


Fuse (5 Amp) 


1^5-79727-3 


Harris: 
3l«320-5 


'^.83 


8 


Fuse Block Assembly 
Consisting of: 


1^5-79727-39 


Harris: 
33000-39 


U.83.1 


12 


Pose (5 Amp) 


1^5-79727-3 


Harris: 
3l»020-5 


1^.83.2 


1 


Fuse Block Assy SbeU 


1^5-79727-61 


Harris: 
33000-61 


l^.8l^ 


8 

1 


Fuse Holder Cover, Each 
with Angle 


1^5-79727-7 
1^5-79727-67 


Harris: 33000-7 


It. 85 


8 

1 


Fuse Holder Cover, 
Each with Angle 


1^5-79727-9 
1^5-79727-67 


Harris: 33000-9 


1^.86 


6 


Fuse (10 Amp) 


1^5-79727-11 


Harris: 3'*020.-10 


l*.87 


2 


Fuse Block Assembly 
Consisting of: 


l^5-79727-l«'7 


Harris: 330o6-l<.T 



MACaSI CM (IOMAII00> 



HATc 20 Jaroiary 196l 
REVISED 



MCDONNELL 



*_x''««etoflr L>oybotd&>n 



PAGE 



66 



ST. LOWS, MISSOUM 



REPORT 



6603-l!«- 



REVISED 




flilM]^t]^f]f|j;||J||^||h i^ --oa Mercury Capsule 






APEEMDIX I-C 








COHTRACTOR-FORMISHED EQUIPMENT - CONTRACTOR INSTAT.T.l! 


B 




ELBCTRICAL (Continued) 










IDENTIFICATIOH 


Item 


Qty. 


Noaenclature 


MAC No. 


Mfg. No. 


U.87.1 


8 


Fuse (10 Anip} 


1*5-79727-11 


Harris: 31*020-10 


^.87.2 


l^ 


Fuse (2^ Anp) 


1*5-79727-13 


Harris: 3l«020-25 


'^.87.3 


1 


Fuse Block Assy Shell 


1*5-79727-63 


Harris: 33000-63 


lv.88 


2 

1 


Fuse Holder Cover, Each 
with Angle 


1*5-79727-17 
1*5-79727-67 


Harris: 33000-17 


U.89 


2 

1 


Fuse Holder Cover, Each 
vlth Angle 


1*5-79727-19 
1*5-79727-67 


Harris: 33000-19 


lf.90 


2 


Fuse Block Assonbly 


1*5-79727-55 


Harris: 33000-55 


U.90.1 


1* 


Fuse (5 Acrp) 


1*5-79727-3 


Harris: 31*020-5 


II-.90.2 


8 


Fuse (10 Anp) 


1*5-79727-11 


Harris: 3l«020-10 


1^.90.3 


1 


Fuse Block Assy Shell 


1*5-79727-65 


Harris: 33000-65 


li-.9l 


2 

1 


Fuse Bolder Cover, 
Each vlth Angle 


1*5-79727-31 
1*5-79727-67 


Harris: 33000-31^ 


lt.92 


2 

1 


Fuse ]folder Cover, Each 
with Angle 


1*5-79727-33 
1*5-79727-67 


Harris: 33000-33 


^.93 


31 


Switch 


1*5-79729-79 


Harris: 3l«000-7 


\.<^ 


1 


Swltch-8 Position ' 
Rotary 


1*5-79731-1 


Harris: 32000-1 


I4..95 


6 


Toggle Switch 


1*5-79732-1 


Cutler -Hanmer : 
8906K983 


1^.96 


21 


Toggle Switch 


1*5-79732-13 


Cutler -Hammer : 
8906K98I* 


1^.9T 


2 


Toggle Switch 


1*5-79732-15 


Cutler-Hammer : 
8906K985 



MAC 231 CM (tOMAItSS) 



HATP 20 January 

REVisa 

REVISH) 



m. mmm^^^ 



iOtdium PAGE ^ 

ST. LOUIS, MISSOUII REPORT 660^^ 

jonnpi Mercury Capsule 



APPENDIX I-C 
COHTRACTOR-FURNISHED EQUIPMEHT - CONTRACTOR INSTALLED 
ELECTRICAL (Continued) 

IDENTIFICATION 



Item 


Qty. 
2 


NomenclatTire 


1^.98 


Toggle Switch 


l*.99 


1 


Plug Assanbly-Anteona 


4.100 


1 


Receptacle Assembly 
Antenna 


Jf.lOl 


5 


Plug Assembly-Retrogra( 
and Adapter 


U.102 


5 


Receptacle Assembly 
Retrograde and Adapter 


U.103 


1 


Panel Assembly, L.H. 
Switch 


4.10ifr 


1 


Flashing Recovery 
Light 


14-. 105 


1 


Maximum Altitude 
Sensor 


1»-.106 


1 


Thrust Cutoff Sensor 



MAC No. 



Mfg. Ho. 



45-79732-25 Cutler-Hammer :- 
8906K986 

45-79736-1 Cannon: 

22037-98 

45-79736-3 Cannon: 
22037-99 

45-79736-9 Cannon: 
22036-96 

45-79736-11 Cannon: 
22037-97 

45-81014-301 - - - 



45-86702-3 ACR Electronics: 
ACEII3-H 

45-87708-15 Donner -Scientific 
7005P 

45-87709-5 Donner-Scientific 
4403-2-300-020 



MAC 291 CM <IOMAItS«l 



„,„ a,..o^x^ MCDONNELL ^ ^^^^^ ,^ « 

REVIStt . ST, tow s, MlSSOUn RETORT §^03:^ 

REVISa ^^* '^^it" iPITf If liMf "* MODa Mercury Capgnl^ 



APPENDIX I-C 

COMIRACTOR-FURWISHED EQUIPMEHT-COHTRACTOR ISSCALLED 

AUTOMATIC STABILIZATION AHD COiaTROL SYSTEM 

IDKMTJJICAriON 

Minneapolis- 
Item Qty. Nomenclataire MAC Ho> Honeyvell No, 

5 Not provided ia Capstile No. Ik. 



MAC 231 CM <10MAfl5S> 



0.^ ^ .«^ 1961 MCDONNELL ^ ^^^^^^ ,^ 69 

REVISB) ST> LOWS. MISSOUM REPORT 66Q3zU 

REVISED AllwlHkaaBJMmMi^*^ MOOB. Mercury Capsule 



APPENDIX I-C 
COIirRACTOR-FUBHISHED EQUirMEBT-COMTRACTOR INSTALLED 
BEACTION COHTROL SYSTEM 

IDENTiyiCATION 
Item Qty> Nomenclatxire MAC No. Mfg> No. 

6 Not provided in Capsxile No. l^i-. 



DATP ao January 196I 

REVISED 

REVISED 



MCDONNELL ^ 



^^y't^ie^tm- Lioybotdtton, 



ST. LOUIS^ MISSOUM 



PAGE — 
REPORT 


6603-U 


AAOOQ.. 


Mercury Capsule 







APPENDIX I-C 








COBTEACrOR-FUElIISHED EQUHMEBT - COMTRACTOR HJSTAILED 




COMMUNICAEIOK SYSTEMS 












IDENTIFICATION 


Item 


Qty. 


Nomenclature 


MAC No. 


Mfg. No. 


7 




CoDnnunications System 
Consisting of: 


»*5-8570O 


Collins: 


7.1 


1 


Panel, Control 


U5-85700-3I 


Collins: 
522 1812 034 


7.2 


1 


Isolator, Bicone 


45-85700-1*3 


Collins : 
522 1963 012 


7.3 


1 


Antenna, LUib' Descent 


1*5-85700-49 


Collins: 
522 1817 015 


7A 


1 


Switch, Coaxial 


45-85700-51 


Trans CO : 
1460 233A 


7.5 


1 


Multiplexer 


45-85700-71 


Microphase: 
7trr69B-l 


7.6 


1 


Transmitter, Telemetry - 
Low Preq. 


45-85700-77 


Texas Instr: 
421923-A4 


7.7 


1 


Transmitter, Telemetry - 
High Freq. 


45-85700-79 


Texas Instr. : 
421923-B3 


7.8 


2 


Power Supply, Telemetry 


45-85700-81 


Texas Instr. : 
421924-3 


7.9 


1 


Line Filter, Telemetry 


45-85700-83 


Collins: 
522 2223 024 


7.10 


1 


Beacon, C-Band Radar 


45-85700-25 


Avion: 
152A200-4Q 


7.11 


3 


Antenna, S and C-Band 


45-85700-33 


Melpar: 
R436158-IA 


7.12 


1 


Power Divider, C-Band 


45-85700-35 


Melpar: 
R5303IO-IA 



MAC 231 CM <tO MAR SSI 



ftA-ff 20 January 1961 
REVfSB) 



MfDOMELL 



*^_^^ca ieteM- Lo^otdtitnt 



PAGE 



71 



ST. LOUIS, MISSOURI 



REPORT 



J6o3rlif 



RFVISED 






}tlB0 AAnnn Mercury Capsule 






APPENDIX I-C 








OOWrRACTOR-PfTRNISHKD EQUIPMENT - 


COHTRACTOE IHSTAT.T.TCTi | 




EHVIIWIIMEHTAL COMTEOL SYSTEM 










IDEirriFICATION 


Item 


Qty. 


Hbmenclature 


MAC No. 


AlResearch No. 


8 




Eavlrozmental Control 
System, Canslsting of: 






8.1 


1 


Tank, Cooling Water 


1*5-83089-1 




8.2 


1 


Control Box 


l^5-83095-l 


510352 Mod. 


8.3 


2 


Cap Assembly, Water Line 


l<.5-83700-69 


PS 173162-1 


8.1f 


1 


Valve, Snorkel Outflow 


1*5-83700-101 


1210lt8 


8.5 


1 


Valve, Snoxkel Inflow 


1*5-83700-211 


12107lf-l 


8.6 


1 


Tube Assembly, HoO 


l*5-83700-2l».l 


171^513 


8.7 


1 


Tube Assembly, HgO 


1*5-81*700-21*3 


17l*511*- 


8.8 


1 


Duct, Cabin Evaporator Steam 


1*5-83700-177 


171^363 


8.9 


1 


2.5 In. MBiman damp 


1*5-83700-255 


1*266 


8.10 


1 


2.31 In. Maiman Clanrp 


1*5-83700-257 


1^365 


8.11 


1 


"0" Blng for Maznan Clamp 
lt5-83700-257 


1*5-83700-265 


s 8057BE-265 


8.12 


2 


"0" Rings 


l*5-83700-2r7 


s 31*690-120 


8.13 


1 


Blower, Cabin Eqioipment 


1*5-83700-1*25 


207990 


8.1l^ 


1 


Freon Orifice for Cabin 
Heat Exchanger 


1*5-83700-1*77 


171+906-2 


8.15 


1 


Heat Elxchanger, for Cabin 
Equipment 


1*5-83700-1*81 


171*260-3 



MAC 131 CM <tOINAII9«l 



DATE 80 January 1961 

REVISED 

REVISH) 



M^DOMELL 



3;7'4^0fa«T Lcyitotd&fjt 



PAGE 



72 



ST. LOWS, MISSOUM 



REPORT 



^^'W 



junna Mercury Capsiile 



Item 
8.16 
8.17 

8.18 
8.19 
8.20 
8.21 



Qty. 

1 
1 

1 
1 
1 
1 



APPENDIX I-C 
COroRACTOR-FURHISHED EQPnMEin! - COITORACTOR INSTALLED 
EMVIKOHMEOTAL COHIBOL SYSTIM (Cont ' d. ) 

IDEITPIFICASPIOH 
Nomenclature 



MAC No. 



Valve, Post Landing Outflow lf5-83700-719 



Valve, Ground Ventilation 
Inlet 

Valve, Cabin Relief 

Line Assembly 

Line Assembly 

Line Assembly 



»^5-83700-723 

lt5-83700-725 
1*5-83010-21 
Jt5-83010-23 
1*5-83010-69 



AlResearch Ho. 

122216-1 

122366-2 

1021*16 



MAC2SI CM (tOMAAMI 



nATP 20 Jantiary 1961 

REVISED 

REVISED 



MDONNELL 



^ute*£^ Loybi 



^ottSdan page 



73 



ST. LOUIS, MISSOUH 



REPORT 



6603-14 



MODPi Mercury Capsule 







APPENDIX I-C 








COHERACTQR-FURIHSHED EQUIPMENT-CONTRACTOR INSTALLET 






INSTRUMENTATION 










HJEHTIFICATION 


Itoa 


Qty. 


Nomenclature 


MAC No. 


Mfg. No. 


9 




Instrumentation System, 
Consisting of: 





. - - 


9.1 


1 


Tape Recorder, Including: 


45-88707-901 


Consolidated 
Elec trodynami c s 
(CEC) 


9.1.1 


1 


Speed Change ELt (1-7/8 ips) 


1+5-88707-13 


CEC 


9.1.2 


1 


Transport Assembly 


45-88707-15 


CEC 


9.1.3 


2 


Reel 


45-88707-17* 


CEC 


9.1. It 


4800 Ft. 


Tape, 1/2 inch 


45-88707-19* 


Minn. Mining & 
Mfg. 197 


9.2 


1 


Instrumentation Package 
"A" Including: 


45-88100-51 


_ _ . 


9.2.1 


1 


Pressure Transducer 


45-88705-5 


_ - _ 


9.2.2 


2 


PDM/PAM C<fflnmitator/Keyer 


45-88709-3 


Gen. Devices: 
1208D-2B 


9.2.3 


1 


D.C. Power Supply, 3V Ifonitor 


45-88203-7 - - - 
MRR No:12QED28 


9.3 


1 


Instrumentation Package 
"B" Tnclurting 


45-88101-51 


- - - 


9.3.1 


2 


Accelerometer, "Y" & 
"X" Axis, + Ug 


45-88712-5 


Donner: 4310-2 


9-3.2 


1 


Accelerometer, "Z" Axis, 
±30g 


45-887IP-3 


Donner: 4310-1 


9.3.3 


2 


Voltage Controlled 
Oscillator -1.3 KE 


45-88700-13 


Dorsett : 
0-aM1.3KD 


*I3iese items to be shipped to launch site for 


installation. 





MAC 231 CM OOMARSal 



^ 



nATP 20 January 1961 

REVISB) 

REVISED 



MCDONNELL 



37'^4tf«^p L^oybotd&n 



9.5 



ST. LOWS, MISSOUM 



PAr^P 


1^ 


WPOBT 


6603-U 


MOOftMerciary Capsule 



APPEHDIX I-C 
COMTRACTOR^-FURMSSED EQUIPMENT -CONI'RACTOR IITSTi^T.T.T!B 
IMSTRUMEHTiCTION (Continued) 

IDENTIPICAriON 



Item 


Qby. 


IfomenclatTxre 


9-3A 


2 


Voltage CozxtroUed 
Oscillator -I.7 IC 


9.3.5 


2 


Voltage Controlled 
Oscillator - 2.3 KC 


9-3.6 


2 


Voltage Controlled 
Oscillator - 10. 5 KC 


9.3.7 


1 


Compensating Oscillator 


9.3.8 


1 


Mixer Amplifier 


9.3.9 


1 


Mixer Anplif ier 


9.3.10 


1 


Voltage Controlled 
Oscillator .560 KC 


9.3.11 


1 


Voltage Controlled 
Oscillator - .730 KC 


9.3.12 


1 


Voltage Controlled 
Oscillator - .960 KC 


9.1^ 


1 


Instrumentation Package 
"C", Including: 


3X,\ 


1 


Solenoid Voltage 
Attenuator 


9-^.2 


1 


Solenoid Voltage 
Attenuator 


9.J^.3 


1 


Instrumentation Assembly 
Rate Signal Filter and 
Calibrate Card 



MAC Hb. 
lf5-88220-9 

U5-88220-11 

i^5-88220-l 

1*5-88700-53 
45-88700-55 
1*5-88217-5 
l(-5-8870O-7 

1*5-88700-9 

1*5-88700-11 

1*5-88102-39 

1*5-88205-7 

1*5-88205-9 

l*5-8821l*-19 

Transducer, Static Pressure 1*5-88705-5 



Mfg. No. 



Dor sett: 20-8M 
Dorsett: ASM-&f 



CBC: l*-38CMa- 
15A 



MAC 231 CM <I0 MAN 9«> 



V 



nATP 20 January 196l 



AKDONNELL 



REVISED 
REVISE) 



^^^^{oMan- L^ybatdSon 



PAGE 



75 



ST. LOUIS, MISSOURI 



REPORT 



6603^lU 



MnnPt Mercury Capsule 



APPEiroiX I'C 
COinaACTOR-FURNISHED EQUIFMEHT - CQITTRACTOR XNSTAT.T.TrD 
LAUDING AMD POST-LAMPING SYSTEM 

IDEHriPICATION 



Item Qty. Momenclature 

10 Landing and Post-Landing 

System^ consisting of: 

10.1 1 Drogue Chute Assembly^ 
consisting of: 



10.1.1 


1 


Drogue Chute 


10.1.2 


1 


Drogue Bag 


10.2 


1 


Mortar Tube 


10.3 


1 


Mortar Sabot 


10. l^ 


1 


Main Cbute Systaa, 
consisting of: 


10.U..1 


1 


Landing Parachute 


IO.I4..2 


1 


Bag, Main Chute Deployment 


10.1I..3 


1 


Lanyard, i^texma 


10.1I..4 


2 


Cutter Beef - k Second 
Reefing 


lO.it.5 


1 


Beefing Line 


10.1I..6 


1 


Bridle Parachute 


10.5 


1 


Reserve Chute System, 
consisting of: 


10.5.1 


1 


Tandlng Parachute 


10.5.2 


1 


Pilot Parachute 



MAC No. 



l»5-ivl700 



Badioplane No. 



if5-UlT00-29» R-5103-309 

i^5-lH700-ll* R-5104 

I>5-1H700-U5* R-5109-309 

lf5-lH700-19» R-5126 

U5-iH700-219» R-5157-321 

1^5-^1700-221* R-5116-305 

i*5-^1700-l8l* R-5135-309 

l^5-^1700-195* 101092-1 

1*5-41700-199* R-5157-95 

1*5-1*1700-201* R-5205-301 

l*5-lH700-219» R-5157-321 

U5-IH700-193* R-5201* 



* These items to he shipped to launch site for Installation. 



MAC 291 CM (to lull 9W 



HATB 20 January 1961 

REVISB) 

REVISB) 



M?DOMELL 



* /x^ gfaa^ Loybotdtion. 



pAce 



76 



ST. LOWS. MISSOUU 



REPORT 



6603-li» 



AAOnW MArwi-ry rapeiila 







APtJsJSDlX I-C 








COOTEACTOR-FURNISHED JsWUHrMENT - COHTRACTOR HBTALLED 




LANDING AND POST-LANDING SYSTEM (Contlntied) 










IDKNTUj-ICATION 


Itoa 
10.5.3 


0*7. 

1 


Nomenclature 

Bag, Reserve Cbute Deploy- 
ment 


MAC No. 
1*5-^1700-225* 


Radloplane No 


R-5117-309 


10.5. »*• 


1 


Laoyard, Pilot Chxzte 


l*5-^1700-ll*9» 


R-5136-301 


10.5.5 


1 


Reefing Line 


1*5-^1700-199* 


R-5157-95 


10.5.6 


2 


Cutter Reef - U Second 
Reefing 


1*5-^1700-195* 


101092-9 


10.6 


2 


Bag, Landing Parachute 
Ejector 


1*5-1*1700-37* 


R-5118-301 


10.7 


2 


Disconnect, Landing Para- 
chute 


1*5-1*1700-191 


R-5127-301 


10.8 


1 


Projectile Assembly, Pilot 
Chute Deploy Gun 


1*5-1*1700-127* 


101070-23 


10.9 


1 


Shear Pin, Pilot Chute 
Deploy Gun 


1*5-1*1700-63* 


101070-17 


10.10 


2 


Baroswltch, 10,600 Ft. 


1*5-1*1700-163 


101080-15 


10.11 


1 


Switch, Inertia 


1*5-1*1700-169 


58215-305 


10.12 


1 


Packet Assembly, Fluorescein 
Dye Marker 


1*5-1*1700-231* 


R-5208 


10.13 


2 


Baroswitch, 1^2,000 Ft. 


1*5-1*1700-165 


101080-17 


10. lU 


2 


Strap Assembly, Adjustable 
Retaining 


1*5-1*1700-101 


R-5195 


10.15 


1 


Strap Non-Adjustable, 
Insulated 


1*5-1*1700-117 


R-5196 


* Tliese 


items to 


be shipped to launch site for installation. 





MAC 291 CM (to MAR SSI 



nATP 20 Jaoaxxary 1961 

REVISED 

REVISED 



MCDONNELL 



^•ZP'^uic^an- L^tybotdtuat 



Item 
10.16 

10.17 

10.18 

10.19 

10.20 

10.21 
10.22 
10.23 
10.21^ 
10.25 
10.26 
10.2T 



ST. LOWS, Missoun 



PAGE 


77 


REPORT 


66o^.Tk 


AAOOa. 


Mercury Capsule 



Qty. 

1 



APPENDIX I-C 
COHPBACTOR-FURHISHED EOmPMSKT - CX)inaACT0R IHSTALLBD 
LAHDIHG AMD POSI-IAMDIHG SY3IM (Continued) 

IDEaiTIFICAIIOH 
nomenclature 



1 
1 
2 
2 

1 
1 
1 



Body Assembly, Gun, Pilot 
Chate Deploy 

Electric Squib, Deployment 
Gun 

Squib Cartridge, Electric 
(Drogue Mortar) 

Cartridge, Sqiiib Electric, 
(Parachute Disconnect) 

Cartridge, Main Charge, 
Deployment Gun 

Gas Generator Assembly 

Gas Generator Assembly 

Cutter Reefing - l6 Second 

Mounting Bracket 

Bag, SQFAR Bomb 

Bridle, Pilot Parachute 

SOFAR Bomb, IXminy 



MAC Ho. 
l^5-lH700-171 

l«.5-iH700-213* 

1*5-41700-211* 

iv5-lH700-2D9» 

1*5-^1700-167* 

1*5-1*1700-239* 
1*5-1*1700-21*1* 

1*5-1*1700-197* 
1*5-1*1700-205 
45-1*1700-227* 
1*5-1*1700-237* 



* These items to be shipped to launch site for installation. 



Radioplane Ho. 
101070-33 

58082 

58081 

58080 

101070-31 

58217-19 

58217-21 

101092-7 

101092-3 

R-5207 

R-5153-301 

PDS-007 



MAC 23t CM (to MAR SS) 



HATc 20 January 1961 
REVtSB) 



M?DONNEll 



^ZP^tote^M- L<oy^otdtcon 



PAGE 



78 



ST. LOWS, Missoun 



REPORT 



f}fTn3-ii» 



REVISED _.. 






^ MnnR Mercury Capsule 






APPENDIX I-C 








COMTEACTOR-FUENISHED EQUIPMEHT - COHTEACfTOR INSTALLED 




FYHarHJHHICS* 












IDEIiriPICATION 


Itaa 


Qty. 


Nomenclature 


MAC No. 


Mfg. No. 


11 




Pyrotechnic Devices, 
Cozislstlng of: 


i^5-72001-lif 




11.1 


♦» 


Squib, Deployment G\m 


1^5-^1700-213 




11.2 


*♦ 


Sqiiib Cartridge, Drogue 
Mortar 


i^5-^1700-211 




11.3 


** 


Gas Generator, Main 
. Chute 


1^5-^1700-215 




•n.x 


** 


Gas Generator, Reserve 
Chute 


1^5-^1700-217 




11.5 


** 


Squib Cartridge, Para- 
chute Disconnect 


lf5-lH700-209 




11.6 


•*» 


Cartridge, Deployment 
Gun 


45-^1700-167 




11.7 


2 


Escplosive Bolt, Clamp 
Ring 


1^5-72702-23 


Olin Matheson: 
II6C-3 


11.8 


\ 


Sscplosive Bolt, Clamp 
Ring 


- 1^5-72702-19 


Olin Matheson: 
112C-7 


11.9 


1 


Ebqplosive Bolt, Retro- 
grade Rocket Ej^^^or 


1^5-72701^-9 


Olin Matheson: 
1130-3 


11.10 


5 


Explosive Disconnect 
Assembly, Consisting of: 


1^5-72705-1 


Beckman-Whitley: 
22I1.3C 


11.10.1 


2 


Explosive Cell 


^^5-72705-5 


Bectanan-Whitley: 
10084 


11.10.2 


1 


Ring Assembly 


1^5-72705-7 


Beclcman-Whitley : 


* Pyrotechnic 


devices to be shipped to launch 


site for installation. 


** Quantities defined under applicable systems, 


t 





M^c aat CM (10 MAW %%\ 



HATP 20 January I96I 

REVISB) 

REVISB) 



\KDONNEU 



^^y^uie^^m- Lcybctdtmi 



PAGE 



79 



ST. LOWS, Ml 




REPORT 



-£6Q3=1Ji- 



UiCS^^ Miayf^iiTy PApgnla 



Item 

11.11.1 
11.11.2 
11.11.3 

11.12 



Q;ty. 



APPEHDIX I-C 
COHTRACTOR-FUBHISHilD EQUXEMEMT - COMTRACTOR CTSTJ^tt.t^ 
PraOIECHMICS* (Continued) 

IDERCIPICATION 
Homenclatxire 



Pyrotechnics Kit 
Cartridge 

Cartridge 

Cartridge 

E^gplosive Ring Dummy 



MAC No. 


Mfg. No. 


i^5-72703-17 







OUn Matheson: 
AED863-I 


— - 


McCormlclc Selph: 
2561 


• • " 


Frankford 

Arsenal: 

M67EI 


1^5-35050-591 


• • M 



* Pyrotechnic devices to be shipped to lavmch site for installation. 



MAC2ai CM (to MAM Ml 



r 



REvtsa 

REVISH) 



MCDONNELL ^ ^/^ 



PAGE 



80 



ST. LOWS, MISSOUM 



REPORT 



Mq2c£^ 



L 



AAnoH, Merciary Capsule 



APPEHDIX I*D 
COMTRAgrOR-FURHISHED EQUIIMEICT-GOVERMMEHT IM3TALLED 
Item Qty> Homenclatiire Wt. Identification 

Not Used 



MAC2SI CM CtOMAMSal